diff --git a/Manifest-v1.11.toml.default b/Manifest-v1.11.toml.default
index 076203da..461b3127 100644
--- a/Manifest-v1.11.toml.default
+++ b/Manifest-v1.11.toml.default
@@ -1,13 +1,13 @@
 # This file is machine-generated - editing it directly is not advised
 
-julia_version = "1.11.4"
+julia_version = "1.11.6"
 manifest_format = "2.0"
-project_hash = "8aabd59bb81f00c0149c8b45c84ed6c3038dd1c6"
+project_hash = "af9326657e0997d9341c6ceac49c14579de5e965"
 
 [[deps.ADTypes]]
-git-tree-sha1 = "e2478490447631aedba0823d4d7a80b2cc8cdb32"
+git-tree-sha1 = "7927b9af540ee964cc5d1b73293f1eb0b761a3a1"
 uuid = "47edcb42-4c32-4615-8424-f2b9edc5f35b"
-version = "1.14.0"
+version = "1.16.0"
 weakdeps = ["ChainRulesCore", "ConstructionBase", "EnzymeCore"]
 
     [deps.ADTypes.extensions]
@@ -41,9 +41,9 @@ version = "0.1.42"
 
 [[deps.Adapt]]
 deps = ["LinearAlgebra", "Requires"]
-git-tree-sha1 = "cd8b948862abee8f3d3e9b73a102a9ca924debb0"
+git-tree-sha1 = "f7817e2e585aa6d924fd714df1e2a84be7896c60"
 uuid = "79e6a3ab-5dfb-504d-930d-738a2a938a0e"
-version = "4.2.0"
+version = "4.3.0"
 weakdeps = ["SparseArrays", "StaticArrays"]
 
     [deps.Adapt.extensions]
@@ -56,9 +56,9 @@ version = "1.1.2"
 
 [[deps.ArrayInterface]]
 deps = ["Adapt", "LinearAlgebra"]
-git-tree-sha1 = "017fcb757f8e921fb44ee063a7aafe5f89b86dd1"
+git-tree-sha1 = "9606d7832795cbef89e06a550475be300364a8aa"
 uuid = "4fba245c-0d91-5ea0-9b3e-6abc04ee57a9"
-version = "7.18.0"
+version = "7.19.0"
 
     [deps.ArrayInterface.extensions]
     ArrayInterfaceBandedMatricesExt = "BandedMatrices"
@@ -87,10 +87,10 @@ version = "7.18.0"
     Tracker = "9f7883ad-71c0-57eb-9f7f-b5c9e6d3789c"
 
 [[deps.ArrayLayouts]]
-deps = ["FillArrays", "LinearAlgebra"]
-git-tree-sha1 = "4e25216b8fea1908a0ce0f5d87368587899f75be"
+deps = ["FillArrays", "LinearAlgebra", "StaticArrays"]
+git-tree-sha1 = "120e392af69350960b1d3b89d41dcc1d66543858"
 uuid = "4c555306-a7a7-4459-81d9-ec55ddd5c99a"
-version = "1.11.1"
+version = "1.11.2"
 weakdeps = ["SparseArrays"]
 
     [deps.ArrayLayouts.extensions]
@@ -118,12 +118,13 @@ version = "0.1.6"
 
 [[deps.BracketingNonlinearSolve]]
 deps = ["CommonSolve", "ConcreteStructs", "NonlinearSolveBase", "PrecompileTools", "Reexport", "SciMLBase"]
-git-tree-sha1 = "95cb19c37ea427617e9795655667712f03058d98"
+git-tree-sha1 = "a9014924595b7a2c1dd14aac516e38fa10ada656"
 uuid = "70df07ce-3d50-431d-a3e7-ca6ddb60ac1e"
-version = "1.1.0"
-weakdeps = ["ForwardDiff"]
+version = "1.3.0"
+weakdeps = ["ChainRulesCore", "ForwardDiff"]
 
     [deps.BracketingNonlinearSolve.extensions]
+    BracketingNonlinearSolveChainRulesCoreExt = ["ChainRulesCore", "ForwardDiff"]
     BracketingNonlinearSolveForwardDiffExt = "ForwardDiff"
 
 [[deps.CPUSummary]]
@@ -134,9 +135,9 @@ version = "0.2.6"
 
 [[deps.ChainRulesCore]]
 deps = ["Compat", "LinearAlgebra"]
-git-tree-sha1 = "1713c74e00545bfe14605d2a2be1712de8fbcb58"
+git-tree-sha1 = "06ee8d1aa558d2833aa799f6f0b31b30cada405f"
 uuid = "d360d2e6-b24c-11e9-a2a3-2a2ae2dbcce4"
-version = "1.25.1"
+version = "1.25.2"
 weakdeps = ["SparseArrays"]
 
     [deps.ChainRulesCore.extensions]
@@ -150,9 +151,9 @@ version = "0.1.13"
 
 [[deps.ColorTypes]]
 deps = ["FixedPointNumbers", "Random"]
-git-tree-sha1 = "c7acce7a7e1078a20a285211dd73cd3941a871d6"
+git-tree-sha1 = "67e11ee83a43eb71ddc950302c53bf33f0690dfe"
 uuid = "3da002f7-5984-5a60-b8a6-cbb66c0b333f"
-version = "0.12.0"
+version = "0.12.1"
 
     [deps.ColorTypes.extensions]
     StyledStringsExt = "StyledStrings"
@@ -162,9 +163,9 @@ version = "0.12.0"
 
 [[deps.Colors]]
 deps = ["ColorTypes", "FixedPointNumbers", "Reexport"]
-git-tree-sha1 = "64e15186f0aa277e174aa81798f7eb8598e0157e"
+git-tree-sha1 = "37ea44092930b1811e666c3bc38065d7d87fcc74"
 uuid = "5ae59095-9a9b-59fe-a467-6f913c188581"
-version = "0.13.0"
+version = "0.13.1"
 
 [[deps.CommonSolve]]
 git-tree-sha1 = "0eee5eb66b1cf62cd6ad1b460238e60e4b09400c"
@@ -184,9 +185,9 @@ version = "1.0.0"
 
 [[deps.Compat]]
 deps = ["TOML", "UUIDs"]
-git-tree-sha1 = "8ae8d32e09f0dcf42a36b90d4e17f5dd2e4c4215"
+git-tree-sha1 = "0037835448781bb46feb39866934e243886d756a"
 uuid = "34da2185-b29b-5c13-b0c7-acf172513d20"
-version = "4.16.0"
+version = "4.18.0"
 weakdeps = ["Dates", "LinearAlgebra"]
 
     [deps.Compat.extensions]
@@ -212,9 +213,9 @@ uuid = "2569d6c7-a4a2-43d3-a901-331e8e4be471"
 version = "0.2.3"
 
 [[deps.ConstructionBase]]
-git-tree-sha1 = "76219f1ed5771adbb096743bff43fb5fdd4c1157"
+git-tree-sha1 = "b4b092499347b18a015186eae3042f72267106cb"
 uuid = "187b0558-2788-49d3-abe0-74a17ed4e7c9"
-version = "1.5.8"
+version = "1.6.0"
 
     [deps.ConstructionBase.extensions]
     ConstructionBaseIntervalSetsExt = "IntervalSets"
@@ -232,16 +233,21 @@ git-tree-sha1 = "fcbb72b032692610bfbdb15018ac16a36cf2e406"
 uuid = "adafc99b-e345-5852-983c-f28acb93d879"
 version = "0.3.1"
 
+[[deps.Crayons]]
+git-tree-sha1 = "249fe38abf76d48563e2f4556bebd215aa317e15"
+uuid = "a8cc5b0e-0ffa-5ad4-8c14-923d3ee1735f"
+version = "4.1.1"
+
 [[deps.DataAPI]]
 git-tree-sha1 = "abe83f3a2f1b857aac70ef8b269080af17764bbe"
 uuid = "9a962f9c-6df0-11e9-0e5d-c546b8b5ee8a"
 version = "1.16.0"
 
 [[deps.DataStructures]]
-deps = ["Compat", "InteractiveUtils", "OrderedCollections"]
-git-tree-sha1 = "1d0a14036acb104d9e89698bd408f63ab58cdc82"
+deps = ["OrderedCollections"]
+git-tree-sha1 = "76b3b7c3925d943edf158ddb7f693ba54eb297a5"
 uuid = "864edb3b-99cc-5e75-8d2d-829cb0a9cfe8"
-version = "0.18.20"
+version = "0.19.0"
 
 [[deps.DataValueInterfaces]]
 git-tree-sha1 = "bfc1187b79289637fa0ef6d4436ebdfe6905cbd6"
@@ -266,10 +272,10 @@ uuid = "8bb1440f-4735-579b-a4ab-409b98df4dab"
 version = "1.9.1"
 
 [[deps.DiffEqBase]]
-deps = ["ArrayInterface", "ConcreteStructs", "DataStructures", "DocStringExtensions", "EnumX", "EnzymeCore", "FastBroadcast", "FastClosures", "FastPower", "FunctionWrappers", "FunctionWrappersWrappers", "LinearAlgebra", "Logging", "Markdown", "MuladdMacro", "Parameters", "PrecompileTools", "Printf", "RecursiveArrayTools", "Reexport", "SciMLBase", "SciMLOperators", "SciMLStructures", "Setfield", "Static", "StaticArraysCore", "Statistics", "TruncatedStacktraces"]
-git-tree-sha1 = "615e8358608628b9768275f4bd8c237724e72f08"
+deps = ["ArrayInterface", "ConcreteStructs", "DataStructures", "DocStringExtensions", "EnumX", "EnzymeCore", "FastBroadcast", "FastClosures", "FastPower", "FunctionWrappers", "FunctionWrappersWrappers", "LinearAlgebra", "Logging", "Markdown", "MuladdMacro", "Parameters", "PrecompileTools", "Printf", "RecursiveArrayTools", "Reexport", "SciMLBase", "SciMLOperators", "SciMLStructures", "Setfield", "Static", "StaticArraysCore", "Statistics", "SymbolicIndexingInterface", "TruncatedStacktraces"]
+git-tree-sha1 = "c1ae1a949a95ee1895e3b48e11982f102152c3aa"
 uuid = "2b5f629d-d688-5b77-993f-72d75c75574e"
-version = "6.164.2"
+version = "6.182.0"
 
     [deps.DiffEqBase.extensions]
     DiffEqBaseCUDAExt = "CUDA"
@@ -282,6 +288,7 @@ version = "6.164.2"
     DiffEqBaseMPIExt = "MPI"
     DiffEqBaseMeasurementsExt = "Measurements"
     DiffEqBaseMonteCarloMeasurementsExt = "MonteCarloMeasurements"
+    DiffEqBaseMooncakeExt = "Mooncake"
     DiffEqBaseReverseDiffExt = "ReverseDiff"
     DiffEqBaseSparseArraysExt = "SparseArrays"
     DiffEqBaseTrackerExt = "Tracker"
@@ -298,6 +305,7 @@ version = "6.164.2"
     MPI = "da04e1cc-30fd-572f-bb4f-1f8673147195"
     Measurements = "eff96d63-e80a-5855-80a2-b1b0885c5ab7"
     MonteCarloMeasurements = "0987c9cc-fe09-11e8-30f0-b96dd679fdca"
+    Mooncake = "da2b9cff-9c12-43a0-ae48-6db2b0edb7d6"
     ReverseDiff = "37e2e3b7-166d-5795-8a7a-e32c996b4267"
     SparseArrays = "2f01184e-e22b-5df5-ae63-d93ebab69eaf"
     Tracker = "9f7883ad-71c0-57eb-9f7f-b5c9e6d3789c"
@@ -317,9 +325,9 @@ version = "1.15.1"
 
 [[deps.DifferentiationInterface]]
 deps = ["ADTypes", "LinearAlgebra"]
-git-tree-sha1 = "479214d2988a837e6d21ac38afdcb03cb2d0994e"
+git-tree-sha1 = "c8d85ecfcbaef899308706bebdd8b00107f3fb43"
 uuid = "a0c0ee7d-e4b9-4e03-894e-1c5f64a51d63"
-version = "0.6.43"
+version = "0.6.54"
 
     [deps.DifferentiationInterface.extensions]
     DifferentiationInterfaceChainRulesCoreExt = "ChainRulesCore"
@@ -329,11 +337,13 @@ version = "0.6.43"
     DifferentiationInterfaceFiniteDiffExt = "FiniteDiff"
     DifferentiationInterfaceFiniteDifferencesExt = "FiniteDifferences"
     DifferentiationInterfaceForwardDiffExt = ["ForwardDiff", "DiffResults"]
+    DifferentiationInterfaceGPUArraysCoreExt = "GPUArraysCore"
     DifferentiationInterfaceGTPSAExt = "GTPSA"
     DifferentiationInterfaceMooncakeExt = "Mooncake"
-    DifferentiationInterfacePolyesterForwardDiffExt = "PolyesterForwardDiff"
+    DifferentiationInterfacePolyesterForwardDiffExt = ["PolyesterForwardDiff", "ForwardDiff", "DiffResults"]
     DifferentiationInterfaceReverseDiffExt = ["ReverseDiff", "DiffResults"]
     DifferentiationInterfaceSparseArraysExt = "SparseArrays"
+    DifferentiationInterfaceSparseConnectivityTracerExt = "SparseConnectivityTracer"
     DifferentiationInterfaceSparseMatrixColoringsExt = "SparseMatrixColorings"
     DifferentiationInterfaceStaticArraysExt = "StaticArrays"
     DifferentiationInterfaceSymbolicsExt = "Symbolics"
@@ -350,11 +360,13 @@ version = "0.6.43"
     FiniteDiff = "6a86dc24-6348-571c-b903-95158fe2bd41"
     FiniteDifferences = "26cc04aa-876d-5657-8c51-4c34ba976000"
     ForwardDiff = "f6369f11-7733-5829-9624-2563aa707210"
+    GPUArraysCore = "46192b85-c4d5-4398-a991-12ede77f4527"
     GTPSA = "b27dd330-f138-47c5-815b-40db9dd9b6e8"
     Mooncake = "da2b9cff-9c12-43a0-ae48-6db2b0edb7d6"
     PolyesterForwardDiff = "98d1487c-24ca-40b6-b7ab-df2af84e126b"
     ReverseDiff = "37e2e3b7-166d-5795-8a7a-e32c996b4267"
     SparseArrays = "2f01184e-e22b-5df5-ae63-d93ebab69eaf"
+    SparseConnectivityTracer = "9f842d2f-2579-4b1d-911e-f412cf18a3f5"
     SparseMatrixColorings = "0a514795-09f3-496d-8182-132a7b665d35"
     StaticArrays = "90137ffa-7385-5640-81b9-e52037218182"
     Symbolics = "0c5d862f-8b57-4792-8d23-62f2024744c7"
@@ -367,10 +379,9 @@ uuid = "8ba89e20-285c-5b6f-9357-94700520ee1b"
 version = "1.11.0"
 
 [[deps.DocStringExtensions]]
-deps = ["LibGit2"]
-git-tree-sha1 = "2fb1e02f2b635d0845df5d7c167fec4dd739b00d"
+git-tree-sha1 = "7442a5dfe1ebb773c29cc2962a8980f47221d76c"
 uuid = "ffbed154-4ef7-542d-bbb7-c09d3a79fcae"
-version = "0.9.3"
+version = "0.9.5"
 
 [[deps.Downloads]]
 deps = ["ArgTools", "FileWatching", "LibCURL", "NetworkOptions"]
@@ -378,14 +389,14 @@ uuid = "f43a241f-c20a-4ad4-852c-f6b1247861c6"
 version = "1.6.0"
 
 [[deps.EnumX]]
-git-tree-sha1 = "bdb1942cd4c45e3c678fd11569d5cccd80976237"
+git-tree-sha1 = "bddad79635af6aec424f53ed8aad5d7555dc6f00"
 uuid = "4e289a0a-7415-4d19-859d-a7e5c4648b56"
-version = "1.0.4"
+version = "1.0.5"
 
 [[deps.EnzymeCore]]
-git-tree-sha1 = "0cdb7af5c39e92d78a0ee8d0a447d32f7593137e"
+git-tree-sha1 = "8272a687bca7b5c601c0c24fc0c71bff10aafdfd"
 uuid = "f151be2c-9106-41f4-ab19-57ee4f262869"
-version = "0.8.8"
+version = "0.8.12"
 weakdeps = ["Adapt"]
 
     [deps.EnzymeCore.extensions]
@@ -413,15 +424,16 @@ uuid = "9aa1b823-49e4-5ca5-8b0f-3971ec8bab6a"
 version = "0.3.2"
 
 [[deps.FastPower]]
-git-tree-sha1 = "58c3431137131577a7c379d00fea00be524338fb"
+git-tree-sha1 = "5f7afd4b1a3969dc34d692da2ed856047325b06e"
 uuid = "a4df4552-cc26-4903-aec0-212e50a0e84b"
-version = "1.1.1"
+version = "1.1.3"
 
     [deps.FastPower.extensions]
     FastPowerEnzymeExt = "Enzyme"
     FastPowerForwardDiffExt = "ForwardDiff"
     FastPowerMeasurementsExt = "Measurements"
     FastPowerMonteCarloMeasurementsExt = "MonteCarloMeasurements"
+    FastPowerMooncakeExt = "Mooncake"
     FastPowerReverseDiffExt = "ReverseDiff"
     FastPowerTrackerExt = "Tracker"
 
@@ -430,6 +442,7 @@ version = "1.1.1"
     ForwardDiff = "f6369f11-7733-5829-9624-2563aa707210"
     Measurements = "eff96d63-e80a-5855-80a2-b1b0885c5ab7"
     MonteCarloMeasurements = "0987c9cc-fe09-11e8-30f0-b96dd679fdca"
+    Mooncake = "da2b9cff-9c12-43a0-ae48-6db2b0edb7d6"
     ReverseDiff = "37e2e3b7-166d-5795-8a7a-e32c996b4267"
     Tracker = "9f7883ad-71c0-57eb-9f7f-b5c9e6d3789c"
 
@@ -479,9 +492,9 @@ version = "0.8.5"
 
 [[deps.ForwardDiff]]
 deps = ["CommonSubexpressions", "DiffResults", "DiffRules", "LinearAlgebra", "LogExpFunctions", "NaNMath", "Preferences", "Printf", "Random", "SpecialFunctions"]
-git-tree-sha1 = "a2df1b776752e3f344e5116c06d75a10436ab853"
+git-tree-sha1 = "910febccb28d493032495b7009dce7d7f7aee554"
 uuid = "f6369f11-7733-5829-9624-2563aa707210"
-version = "0.10.38"
+version = "1.0.1"
 weakdeps = ["StaticArrays"]
 
     [deps.ForwardDiff.extensions]
@@ -516,9 +529,9 @@ version = "0.1.1"
 
 [[deps.IntelOpenMP_jll]]
 deps = ["Artifacts", "JLLWrappers", "LazyArtifacts", "Libdl"]
-git-tree-sha1 = "0f14a5456bdc6b9731a5682f439a672750a09e48"
+git-tree-sha1 = "ec1debd61c300961f98064cfb21287613ad7f303"
 uuid = "1d5cc7b8-4909-519e-a0f8-d0f5ad9712d0"
-version = "2025.0.4+0"
+version = "2025.2.0+0"
 
 [[deps.InteractiveUtils]]
 deps = ["Markdown"]
@@ -527,14 +540,16 @@ version = "1.11.0"
 
 [[deps.Interpolations]]
 deps = ["Adapt", "AxisAlgorithms", "ChainRulesCore", "LinearAlgebra", "OffsetArrays", "Random", "Ratios", "Requires", "SharedArrays", "SparseArrays", "StaticArrays", "WoodburyMatrices"]
-git-tree-sha1 = "88a101217d7cb38a7b481ccd50d21876e1d1b0e0"
+git-tree-sha1 = "f2905febca224eade352a573e129ef43aa593354"
 uuid = "a98d9a8b-a2ab-59e6-89dd-64a1c18fca59"
-version = "0.15.1"
+version = "0.16.1"
 
     [deps.Interpolations.extensions]
+    InterpolationsForwardDiffExt = "ForwardDiff"
     InterpolationsUnitfulExt = "Unitful"
 
     [deps.Interpolations.weakdeps]
+    ForwardDiff = "f6369f11-7733-5829-9624-2563aa707210"
     Unitful = "1986cc42-f94f-5a68-af5c-568840ba703d"
 
 [[deps.InverseFunctions]]
@@ -562,9 +577,9 @@ version = "1.0.0"
 
 [[deps.JLLWrappers]]
 deps = ["Artifacts", "Preferences"]
-git-tree-sha1 = "a007feb38b422fbdab534406aeca1b86823cb4d6"
+git-tree-sha1 = "0533e564aae234aff59ab625543145446d8b6ec2"
 uuid = "692b3bcd-3c85-4b1f-b108-f13ce0eb3210"
-version = "1.7.0"
+version = "1.7.1"
 
 [[deps.Jieko]]
 deps = ["ExproniconLite"]
@@ -574,9 +589,9 @@ version = "0.2.1"
 
 [[deps.Krylov]]
 deps = ["LinearAlgebra", "Printf", "SparseArrays"]
-git-tree-sha1 = "b29d37ce30fa401a4563b18880ab91f979a29734"
+git-tree-sha1 = "b94257a1a8737099ca40bc7271a8b374033473ed"
 uuid = "ba0b0d4f-ebba-5204-a429-3ac8c609bfb7"
-version = "0.9.10"
+version = "0.10.1"
 
 [[deps.LaTeXStrings]]
 git-tree-sha1 = "dda21b8cbd6a6c40d9d02a73230f9d70fed6918c"
@@ -591,9 +606,9 @@ version = "0.1.17"
 
 [[deps.LazyArrays]]
 deps = ["ArrayLayouts", "FillArrays", "LinearAlgebra", "MacroTools", "SparseArrays"]
-git-tree-sha1 = "866ce84b15e54d758c11946aacd4e5df0e60b7a3"
+git-tree-sha1 = "76627adb8c542c6b73f68d4bfd0aa71c9893a079"
 uuid = "5078a376-72f3-5289-bfd5-ec5146d43c02"
-version = "2.6.1"
+version = "2.6.2"
 
     [deps.LazyArrays.extensions]
     LazyArraysBandedMatricesExt = "BandedMatrices"
@@ -641,6 +656,12 @@ version = "1.11.0+1"
 uuid = "8f399da3-3557-5675-b5ff-fb832c97cbdb"
 version = "1.11.0"
 
+[[deps.Libiconv_jll]]
+deps = ["Artifacts", "JLLWrappers", "Libdl"]
+git-tree-sha1 = "be484f5c92fad0bd8acfef35fe017900b0b73809"
+uuid = "94ce4f54-9a6c-5748-9c1c-f9c7231a4531"
+version = "1.18.0+0"
+
 [[deps.LineSearch]]
 deps = ["ADTypes", "CommonSolve", "ConcreteStructs", "FastClosures", "LinearAlgebra", "MaybeInplace", "SciMLBase", "SciMLJacobianOperators", "StaticArraysCore"]
 git-tree-sha1 = "97d502765cc5cf3a722120f50da03c2474efce04"
@@ -660,18 +681,21 @@ version = "1.11.0"
 
 [[deps.LinearSolve]]
 deps = ["ArrayInterface", "ChainRulesCore", "ConcreteStructs", "DocStringExtensions", "EnumX", "GPUArraysCore", "InteractiveUtils", "Krylov", "LazyArrays", "Libdl", "LinearAlgebra", "MKL_jll", "Markdown", "PrecompileTools", "Preferences", "RecursiveArrayTools", "Reexport", "SciMLBase", "SciMLOperators", "Setfield", "StaticArraysCore", "UnPack"]
-git-tree-sha1 = "6e975dea0fc1825ef3bc83c11281fdf745a69a43"
+git-tree-sha1 = "4a7614717945ce05d1693192f399e3b258c60636"
 uuid = "7ed4a6bd-45f5-4d41-b270-4a48e9bafcae"
-version = "3.4.0"
+version = "3.25.1"
 
     [deps.LinearSolve.extensions]
+    LinearSolveBLISExt = ["blis_jll", "LAPACK_jll"]
     LinearSolveBandedMatricesExt = "BandedMatrices"
     LinearSolveBlockDiagonalsExt = "BlockDiagonals"
     LinearSolveCUDAExt = "CUDA"
     LinearSolveCUDSSExt = "CUDSS"
+    LinearSolveCUSOLVERRFExt = ["CUSOLVERRF", "SparseArrays"]
     LinearSolveEnzymeExt = "EnzymeCore"
     LinearSolveFastAlmostBandedMatricesExt = "FastAlmostBandedMatrices"
     LinearSolveFastLapackInterfaceExt = "FastLapackInterface"
+    LinearSolveForwardDiffExt = "ForwardDiff"
     LinearSolveHYPREExt = "HYPRE"
     LinearSolveIterativeSolversExt = "IterativeSolvers"
     LinearSolveKernelAbstractionsExt = "KernelAbstractions"
@@ -687,18 +711,22 @@ version = "3.4.0"
     BlockDiagonals = "0a1fb500-61f7-11e9-3c65-f5ef3456f9f0"
     CUDA = "052768ef-5323-5732-b1bb-66c8b64840ba"
     CUDSS = "45b445bb-4962-46a0-9369-b4df9d0f772e"
+    CUSOLVERRF = "a8cc9031-bad2-4722-94f5-40deabb4245c"
     EnzymeCore = "f151be2c-9106-41f4-ab19-57ee4f262869"
     FastAlmostBandedMatrices = "9d29842c-ecb8-4973-b1e9-a27b1157504e"
     FastLapackInterface = "29a986be-02c6-4525-aec4-84b980013641"
+    ForwardDiff = "f6369f11-7733-5829-9624-2563aa707210"
     HYPRE = "b5ffcf37-a2bd-41ab-a3da-4bd9bc8ad771"
     IterativeSolvers = "42fd0dbc-a981-5370-80f2-aaf504508153"
     KernelAbstractions = "63c18a36-062a-441e-b654-da1e3ab1ce7c"
     KrylovKit = "0b1a1467-8014-51b9-945f-bf0ae24f4b77"
+    LAPACK_jll = "51474c39-65e3-53ba-86ba-03b1b862ec14"
     Metal = "dde4c033-4e86-420c-a63e-0dd931031962"
     Pardiso = "46dd5b70-b6fb-5a00-ae2d-e8fea33afaf2"
     RecursiveFactorization = "f2c3362d-daeb-58d1-803e-2bc74f2840b4"
     SparseArrays = "2f01184e-e22b-5df5-ae63-d93ebab69eaf"
     Sparspak = "e56a9233-b9d6-4f03-8d0f-1825330902ac"
+    blis_jll = "6136c539-28a5-5bf0-87cc-b183200dce32"
 
 [[deps.LogExpFunctions]]
 deps = ["DocStringExtensions", "IrrationalConstants", "LinearAlgebra"]
@@ -722,14 +750,14 @@ version = "1.11.0"
 
 [[deps.MKL_jll]]
 deps = ["Artifacts", "IntelOpenMP_jll", "JLLWrappers", "LazyArtifacts", "Libdl", "oneTBB_jll"]
-git-tree-sha1 = "5de60bc6cb3899cd318d80d627560fae2e2d99ae"
+git-tree-sha1 = "282cadc186e7b2ae0eeadbd7a4dffed4196ae2aa"
 uuid = "856f044c-d86e-5d09-b602-aeab76dc8ba7"
-version = "2025.0.1+1"
+version = "2025.2.0+0"
 
 [[deps.MacroTools]]
-git-tree-sha1 = "72aebe0b5051e5143a079a4685a46da330a40472"
+git-tree-sha1 = "1e0228a030642014fe5cfe68c2c0a818f9e3f522"
 uuid = "1914dd2f-81c6-5fcd-8719-6d5c9610ff09"
-version = "0.5.15"
+version = "0.5.16"
 
 [[deps.ManualMemory]]
 git-tree-sha1 = "bcaef4fc7a0cfe2cba636d84cda54b5e4e4ca3cd"
@@ -767,9 +795,9 @@ version = "1.11.0"
 
 [[deps.Moshi]]
 deps = ["ExproniconLite", "Jieko"]
-git-tree-sha1 = "453de0fc2be3d11b9b93ca4d0fddd91196dcf1ed"
+git-tree-sha1 = "53f817d3e84537d84545e0ad749e483412dd6b2a"
 uuid = "2e0e35c7-a2e4-4343-998d-7ef72827ed2d"
-version = "0.3.5"
+version = "0.3.7"
 
 [[deps.MozillaCACerts_jll]]
 uuid = "14a3606d-f60d-562e-9121-12d972cd8159"
@@ -782,9 +810,9 @@ version = "0.2.4"
 
 [[deps.NaNMath]]
 deps = ["OpenLibm_jll"]
-git-tree-sha1 = "cc0a5deefdb12ab3a096f00a6d42133af4560d71"
+git-tree-sha1 = "9b8215b1ee9e78a293f99797cd31375471b2bcae"
 uuid = "77ba4419-2d1f-58cd-9bb1-8ffee604a2e3"
-version = "1.1.2"
+version = "1.1.3"
 
 [[deps.NetworkOptions]]
 uuid = "ca575930-c2e3-43a9-ace4-1e988b2c1908"
@@ -792,9 +820,9 @@ version = "1.2.0"
 
 [[deps.NonlinearSolve]]
 deps = ["ADTypes", "ArrayInterface", "BracketingNonlinearSolve", "CommonSolve", "ConcreteStructs", "DiffEqBase", "DifferentiationInterface", "FastClosures", "FiniteDiff", "ForwardDiff", "LineSearch", "LinearAlgebra", "LinearSolve", "NonlinearSolveBase", "NonlinearSolveFirstOrder", "NonlinearSolveQuasiNewton", "NonlinearSolveSpectralMethods", "PrecompileTools", "Preferences", "Reexport", "SciMLBase", "SimpleNonlinearSolve", "SparseArrays", "SparseMatrixColorings", "StaticArraysCore", "SymbolicIndexingInterface"]
-git-tree-sha1 = "95def4e218a6832d158feafb9963be0337ea432c"
+git-tree-sha1 = "d2ec18c1e4eccbb70b64be2435fc3b06fbcdc0a1"
 uuid = "8913a72c-1f9b-4ce2-8d82-65094dcecaec"
-version = "4.4.0"
+version = "4.10.0"
 
     [deps.NonlinearSolve.extensions]
     NonlinearSolveFastLevenbergMarquardtExt = "FastLevenbergMarquardt"
@@ -824,9 +852,9 @@ version = "4.4.0"
 
 [[deps.NonlinearSolveBase]]
 deps = ["ADTypes", "Adapt", "ArrayInterface", "CommonSolve", "Compat", "ConcreteStructs", "DifferentiationInterface", "EnzymeCore", "FastClosures", "LinearAlgebra", "Markdown", "MaybeInplace", "Preferences", "Printf", "RecursiveArrayTools", "SciMLBase", "SciMLJacobianOperators", "SciMLOperators", "StaticArraysCore", "SymbolicIndexingInterface", "TimerOutputs"]
-git-tree-sha1 = "8a2437b5ead050301b6a6258f226e5137e511000"
+git-tree-sha1 = "1d42a315ba627ca0027d49d0efb44e3d88db24aa"
 uuid = "be0214bd-f91f-a760-ac4e-3421ce2b2da0"
-version = "1.5.0"
+version = "1.14.0"
 
     [deps.NonlinearSolveBase.extensions]
     NonlinearSolveBaseBandedMatricesExt = "BandedMatrices"
@@ -848,15 +876,15 @@ version = "1.5.0"
 
 [[deps.NonlinearSolveFirstOrder]]
 deps = ["ADTypes", "ArrayInterface", "CommonSolve", "ConcreteStructs", "DiffEqBase", "FiniteDiff", "ForwardDiff", "LineSearch", "LinearAlgebra", "LinearSolve", "MaybeInplace", "NonlinearSolveBase", "PrecompileTools", "Reexport", "SciMLBase", "SciMLJacobianOperators", "Setfield", "StaticArraysCore"]
-git-tree-sha1 = "aade7ab02ee4c80ec30dc8a2874fc67155c935f1"
+git-tree-sha1 = "3f1198ae5cbf21e84b8251a9e62fa1f888f3e4cb"
 uuid = "5959db7a-ea39-4486-b5fe-2dd0bf03d60d"
-version = "1.3.0"
+version = "1.7.0"
 
 [[deps.NonlinearSolveQuasiNewton]]
 deps = ["ArrayInterface", "CommonSolve", "ConcreteStructs", "DiffEqBase", "LinearAlgebra", "LinearSolve", "MaybeInplace", "NonlinearSolveBase", "PrecompileTools", "Reexport", "SciMLBase", "SciMLOperators", "StaticArraysCore"]
-git-tree-sha1 = "44a132cb32aeafcb35a6238fd91a2f3f8ff5c5b0"
+git-tree-sha1 = "40dfaf1bf74f1f700f81d0002d4dd90999598eb2"
 uuid = "9a2c21bd-3a47-402d-9113-8faf9a0ee114"
-version = "1.2.0"
+version = "1.8.0"
 weakdeps = ["ForwardDiff"]
 
     [deps.NonlinearSolveQuasiNewton.extensions]
@@ -864,18 +892,18 @@ weakdeps = ["ForwardDiff"]
 
 [[deps.NonlinearSolveSpectralMethods]]
 deps = ["CommonSolve", "ConcreteStructs", "DiffEqBase", "LineSearch", "MaybeInplace", "NonlinearSolveBase", "PrecompileTools", "Reexport", "SciMLBase"]
-git-tree-sha1 = "f28b1ab17b5f15eb2b174eaf8813cf17f0b3e6c0"
+git-tree-sha1 = "84de5a469e119eb2c22ae07c543dc4e7f7001ee7"
 uuid = "26075421-4e9a-44e1-8bd1-420ed7ad02b2"
-version = "1.1.0"
+version = "1.3.0"
 weakdeps = ["ForwardDiff"]
 
     [deps.NonlinearSolveSpectralMethods.extensions]
     NonlinearSolveSpectralMethodsForwardDiffExt = "ForwardDiff"
 
 [[deps.OffsetArrays]]
-git-tree-sha1 = "5e1897147d1ff8d98883cda2be2187dcf57d8f0c"
+git-tree-sha1 = "117432e406b5c023f665fa73dc26e79ec3630151"
 uuid = "6fe1bfb0-de20-5000-8ca7-80f57d26f881"
-version = "1.15.0"
+version = "1.17.0"
 weakdeps = ["Adapt"]
 
     [deps.OffsetArrays.extensions]
@@ -889,7 +917,7 @@ version = "0.3.27+1"
 [[deps.OpenLibm_jll]]
 deps = ["Artifacts", "Libdl"]
 uuid = "05823500-19ac-5b8b-9628-191a04bc5112"
-version = "0.8.1+4"
+version = "0.8.5+0"
 
 [[deps.OpenSpecFun_jll]]
 deps = ["Artifacts", "CompilerSupportLibraries_jll", "JLLWrappers", "Libdl"]
@@ -898,9 +926,9 @@ uuid = "efe28fd5-8261-553b-a9e1-b2916fc3738e"
 version = "0.5.6+0"
 
 [[deps.OrderedCollections]]
-git-tree-sha1 = "cc4054e898b852042d7b503313f7ad03de99c3dd"
+git-tree-sha1 = "05868e21324cede2207c6f0f466b4bfef6d5e7ee"
 uuid = "bac558e1-5e72-5ebc-8fee-abe8a469f55d"
-version = "1.8.0"
+version = "1.8.1"
 
 [[deps.Parameters]]
 deps = ["OrderedCollections", "UnPack"]
@@ -921,9 +949,9 @@ version = "1.11.0"
 
 [[deps.Polyester]]
 deps = ["ArrayInterface", "BitTwiddlingConvenienceFunctions", "CPUSummary", "IfElse", "ManualMemory", "PolyesterWeave", "Static", "StaticArrayInterface", "StrideArraysCore", "ThreadingUtilities"]
-git-tree-sha1 = "6d38fea02d983051776a856b7df75b30cf9a3c1f"
+git-tree-sha1 = "6f7cd22a802094d239824c57d94c8e2d0f7cfc7d"
 uuid = "f517fe37-dbe3-4b94-8317-1923a5111588"
-version = "0.7.16"
+version = "0.7.18"
 
 [[deps.PolyesterWeave]]
 deps = ["BitTwiddlingConvenienceFunctions", "CPUSummary", "IfElse", "Static", "ThreadingUtilities"]
@@ -931,6 +959,20 @@ git-tree-sha1 = "645bed98cd47f72f67316fd42fc47dee771aefcd"
 uuid = "1d0040c9-8b98-4ee7-8388-3f51789ca0ad"
 version = "0.2.2"
 
+[[deps.PreallocationTools]]
+deps = ["Adapt", "ArrayInterface", "ForwardDiff"]
+git-tree-sha1 = "2cc315bb7f6e4d59081bad744cdb911d6374fc7f"
+uuid = "d236fae5-4411-538c-8e31-a6e3d9e00b46"
+version = "0.4.29"
+
+    [deps.PreallocationTools.extensions]
+    PreallocationToolsReverseDiffExt = "ReverseDiff"
+    PreallocationToolsSparseConnectivityTracerExt = "SparseConnectivityTracer"
+
+    [deps.PreallocationTools.weakdeps]
+    ReverseDiff = "37e2e3b7-166d-5795-8a7a-e32c996b4267"
+    SparseConnectivityTracer = "9f842d2f-2579-4b1d-911e-f412cf18a3f5"
+
 [[deps.PrecompileTools]]
 deps = ["Preferences"]
 git-tree-sha1 = "5aa36f7049a63a1528fe8f7c3f2113413ffd4e1f"
@@ -943,6 +985,12 @@ git-tree-sha1 = "9306f6085165d270f7e3db02af26a400d580f5c6"
 uuid = "21216c6a-2e73-6563-6e65-726566657250"
 version = "1.4.3"
 
+[[deps.PrettyTables]]
+deps = ["Crayons", "LaTeXStrings", "Markdown", "PrecompileTools", "Printf", "Reexport", "StringManipulation", "Tables"]
+git-tree-sha1 = "1101cd475833706e4d0e7b122218257178f48f34"
+uuid = "08abe8d2-0d0c-5749-adfa-8a2ac140af0d"
+version = "2.4.0"
+
 [[deps.Printf]]
 deps = ["Unicode"]
 uuid = "de0858da-6303-5e67-8744-51eddeeeb8d7"
@@ -971,13 +1019,14 @@ version = "1.3.4"
 
 [[deps.RecursiveArrayTools]]
 deps = ["Adapt", "ArrayInterface", "DocStringExtensions", "GPUArraysCore", "IteratorInterfaceExtensions", "LinearAlgebra", "RecipesBase", "StaticArraysCore", "Statistics", "SymbolicIndexingInterface", "Tables"]
-git-tree-sha1 = "e96b644f7bfbf1015f8e42a7c7abfae2a48fafbf"
+git-tree-sha1 = "f8726bd5a8b7f5f5d3f6c0ce4793454a599b5243"
 uuid = "731186ca-8d62-57ce-b412-fbd966d074cd"
-version = "3.31.0"
+version = "3.36.0"
 
     [deps.RecursiveArrayTools.extensions]
     RecursiveArrayToolsFastBroadcastExt = "FastBroadcast"
     RecursiveArrayToolsForwardDiffExt = "ForwardDiff"
+    RecursiveArrayToolsKernelAbstractionsExt = "KernelAbstractions"
     RecursiveArrayToolsMeasurementsExt = "Measurements"
     RecursiveArrayToolsMonteCarloMeasurementsExt = "MonteCarloMeasurements"
     RecursiveArrayToolsReverseDiffExt = ["ReverseDiff", "Zygote"]
@@ -989,6 +1038,7 @@ version = "3.31.0"
     [deps.RecursiveArrayTools.weakdeps]
     FastBroadcast = "7034ab61-46d4-4ed7-9d0f-46aef9175898"
     ForwardDiff = "f6369f11-7733-5829-9624-2563aa707210"
+    KernelAbstractions = "63c18a36-062a-441e-b654-da1e3ab1ce7c"
     Measurements = "eff96d63-e80a-5855-80a2-b1b0885c5ab7"
     MonteCarloMeasurements = "0987c9cc-fe09-11e8-30f0-b96dd679fdca"
     ReverseDiff = "37e2e3b7-166d-5795-8a7a-e32c996b4267"
@@ -1010,9 +1060,9 @@ version = "1.3.1"
 
 [[deps.RuntimeGeneratedFunctions]]
 deps = ["ExprTools", "SHA", "Serialization"]
-git-tree-sha1 = "04c968137612c4a5629fa531334bb81ad5680f00"
+git-tree-sha1 = "86a8a8b783481e1ea6b9c91dd949cb32191f8ab4"
 uuid = "7e49a35a-f44a-4d26-94aa-eba1b4ca6b47"
-version = "0.5.13"
+version = "0.5.15"
 
 [[deps.SHA]]
 uuid = "ea8e919c-243c-51af-8825-aaa63cd721ce"
@@ -1024,10 +1074,10 @@ uuid = "94e857df-77ce-4151-89e5-788b33177be4"
 version = "0.1.0"
 
 [[deps.SciMLBase]]
-deps = ["ADTypes", "Accessors", "ArrayInterface", "CommonSolve", "ConstructionBase", "Distributed", "DocStringExtensions", "EnumX", "FunctionWrappersWrappers", "IteratorInterfaceExtensions", "LinearAlgebra", "Logging", "Markdown", "Moshi", "PrecompileTools", "Preferences", "Printf", "RecipesBase", "RecursiveArrayTools", "Reexport", "RuntimeGeneratedFunctions", "SciMLOperators", "SciMLStructures", "StaticArraysCore", "Statistics", "SymbolicIndexingInterface"]
-git-tree-sha1 = "ee305515b0946db5f56af699e8b5804fee04146c"
+deps = ["ADTypes", "Accessors", "Adapt", "ArrayInterface", "CommonSolve", "ConstructionBase", "Distributed", "DocStringExtensions", "EnumX", "FunctionWrappersWrappers", "IteratorInterfaceExtensions", "LinearAlgebra", "Logging", "Markdown", "Moshi", "PrecompileTools", "Preferences", "Printf", "RecipesBase", "RecursiveArrayTools", "Reexport", "RuntimeGeneratedFunctions", "SciMLOperators", "SciMLStructures", "StaticArraysCore", "Statistics", "SymbolicIndexingInterface"]
+git-tree-sha1 = "c056c723b68700fec386dfde8c577089df720c8e"
 uuid = "0bca4576-84f4-4d90-8ffe-ffa030f20462"
-version = "2.75.1"
+version = "2.108.0"
 
     [deps.SciMLBase.extensions]
     SciMLBaseChainRulesCoreExt = "ChainRulesCore"
@@ -1037,7 +1087,7 @@ version = "2.75.1"
     SciMLBasePyCallExt = "PyCall"
     SciMLBasePythonCallExt = "PythonCall"
     SciMLBaseRCallExt = "RCall"
-    SciMLBaseZygoteExt = "Zygote"
+    SciMLBaseZygoteExt = ["Zygote", "ChainRulesCore"]
 
     [deps.SciMLBase.weakdeps]
     ChainRules = "082447d4-558c-5d27-93f4-14fc19e9eca2"
@@ -1052,15 +1102,15 @@ version = "2.75.1"
 
 [[deps.SciMLJacobianOperators]]
 deps = ["ADTypes", "ArrayInterface", "ConcreteStructs", "ConstructionBase", "DifferentiationInterface", "FastClosures", "LinearAlgebra", "SciMLBase", "SciMLOperators"]
-git-tree-sha1 = "f66048bb969e67bd7d1bdd03cd0b81219642bbd0"
+git-tree-sha1 = "3414071e3458f3065de7fa5aed55283b236b4907"
 uuid = "19f34311-ddf3-4b8b-af20-060888a46c0e"
-version = "0.1.1"
+version = "0.1.8"
 
 [[deps.SciMLOperators]]
 deps = ["Accessors", "ArrayInterface", "DocStringExtensions", "LinearAlgebra", "MacroTools"]
-git-tree-sha1 = "6149620767866d4b0f0f7028639b6e661b6a1e44"
+git-tree-sha1 = "7d3a1519dc4d433a6b20035eaff20bde8be77c66"
 uuid = "c0aeaf25-5076-4817-a8d5-81caf7dfa961"
-version = "0.3.12"
+version = "1.4.0"
 weakdeps = ["SparseArrays", "StaticArraysCore"]
 
     [deps.SciMLOperators.extensions]
@@ -1090,9 +1140,9 @@ version = "1.11.0"
 
 [[deps.SimpleNonlinearSolve]]
 deps = ["ADTypes", "ArrayInterface", "BracketingNonlinearSolve", "CommonSolve", "ConcreteStructs", "DifferentiationInterface", "FastClosures", "FiniteDiff", "ForwardDiff", "LineSearch", "LinearAlgebra", "MaybeInplace", "NonlinearSolveBase", "PrecompileTools", "Reexport", "SciMLBase", "Setfield", "StaticArraysCore"]
-git-tree-sha1 = "a3868a6add9f5989d1f4bd21de0333ef89fb9d9f"
+git-tree-sha1 = "09d986e27a606f172c5b6cffbd8b8b2f10bf1c75"
 uuid = "727e6d20-b764-4bd8-a329-72de5adea6c7"
-version = "2.1.0"
+version = "2.7.0"
 
     [deps.SimpleNonlinearSolve.extensions]
     SimpleNonlinearSolveChainRulesCoreExt = "ChainRulesCore"
@@ -1116,20 +1166,26 @@ uuid = "2f01184e-e22b-5df5-ae63-d93ebab69eaf"
 version = "1.11.0"
 
 [[deps.SparseMatrixColorings]]
-deps = ["ADTypes", "DataStructures", "DocStringExtensions", "LinearAlgebra", "Random", "SparseArrays"]
-git-tree-sha1 = "e0ae9189392572abe85bc9fd4ce35e772b1e1e10"
+deps = ["ADTypes", "DocStringExtensions", "LinearAlgebra", "PrecompileTools", "Random", "SparseArrays"]
+git-tree-sha1 = "9de43e0b9b976f1019bf7a879a686c4514520078"
 uuid = "0a514795-09f3-496d-8182-132a7b665d35"
-version = "0.4.14"
-weakdeps = ["Colors"]
+version = "0.4.21"
 
     [deps.SparseMatrixColorings.extensions]
+    SparseMatrixColoringsCUDAExt = "CUDA"
+    SparseMatrixColoringsCliqueTreesExt = "CliqueTrees"
     SparseMatrixColoringsColorsExt = "Colors"
 
+    [deps.SparseMatrixColorings.weakdeps]
+    CUDA = "052768ef-5323-5732-b1bb-66c8b64840ba"
+    CliqueTrees = "60701a23-6482-424a-84db-faee86b9b1f8"
+    Colors = "5ae59095-9a9b-59fe-a467-6f913c188581"
+
 [[deps.SpecialFunctions]]
 deps = ["IrrationalConstants", "LogExpFunctions", "OpenLibm_jll", "OpenSpecFun_jll"]
-git-tree-sha1 = "64cca0c26b4f31ba18f13f6c12af7c85f478cfde"
+git-tree-sha1 = "41852b8679f78c8d8961eeadc8f62cef861a52e3"
 uuid = "276daf66-3868-5448-9aa4-cd146d93841b"
-version = "2.5.0"
+version = "2.5.1"
 weakdeps = ["ChainRulesCore"]
 
     [deps.SpecialFunctions.extensions]
@@ -1137,9 +1193,9 @@ weakdeps = ["ChainRulesCore"]
 
 [[deps.Static]]
 deps = ["CommonWorldInvalidations", "IfElse", "PrecompileTools"]
-git-tree-sha1 = "87d51a3ee9a4b0d2fe054bdd3fc2436258db2603"
+git-tree-sha1 = "f737d444cb0ad07e61b3c1bef8eb91203c321eff"
 uuid = "aedffcd0-7271-4cad-89d0-dc628f76c6d3"
-version = "1.1.1"
+version = "1.2.0"
 
 [[deps.StaticArrayInterface]]
 deps = ["ArrayInterface", "Compat", "IfElse", "LinearAlgebra", "PrecompileTools", "Static"]
@@ -1154,9 +1210,9 @@ weakdeps = ["OffsetArrays", "StaticArrays"]
 
 [[deps.StaticArrays]]
 deps = ["LinearAlgebra", "PrecompileTools", "Random", "StaticArraysCore"]
-git-tree-sha1 = "0feb6b9031bd5c51f9072393eb5ab3efd31bf9e4"
+git-tree-sha1 = "cbea8a6bd7bed51b1619658dec70035e07b8502f"
 uuid = "90137ffa-7385-5640-81b9-e52037218182"
-version = "1.9.13"
+version = "1.9.14"
 weakdeps = ["ChainRulesCore", "Statistics"]
 
     [deps.StaticArrays.extensions]
@@ -1184,16 +1240,33 @@ git-tree-sha1 = "f35f6ab602df8413a50c4a25ca14de821e8605fb"
 uuid = "7792a7ef-975c-4747-a70f-980b88e8d1da"
 version = "0.5.7"
 
+[[deps.StringEncodings]]
+deps = ["Libiconv_jll"]
+git-tree-sha1 = "b765e46ba27ecf6b44faf70df40c57aa3a547dcb"
+uuid = "69024149-9ee7-55f6-a4c4-859efe599b68"
+version = "0.3.7"
+
+[[deps.StringManipulation]]
+deps = ["PrecompileTools"]
+git-tree-sha1 = "725421ae8e530ec29bcbdddbe91ff8053421d023"
+uuid = "892a3eda-7b42-436c-8928-eab12a02cf0e"
+version = "0.4.1"
+
+[[deps.StructMapping]]
+git-tree-sha1 = "42f7869cc68f9a83e33ce6a3e408c774900a37e3"
+uuid = "7c3b921d-20d6-4eba-ad57-605525e86ab2"
+version = "0.2.3"
+
 [[deps.SuiteSparse_jll]]
 deps = ["Artifacts", "Libdl", "libblastrampoline_jll"]
 uuid = "bea87d4a-7f5b-5778-9afe-8cc45184846c"
 version = "7.7.0+0"
 
 [[deps.SymbolicIndexingInterface]]
-deps = ["Accessors", "ArrayInterface", "RuntimeGeneratedFunctions", "StaticArraysCore"]
-git-tree-sha1 = "d6c04e26aa1c8f7d144e1a8c47f1c73d3013e289"
+deps = ["Accessors", "ArrayInterface", "PrettyTables", "RuntimeGeneratedFunctions", "StaticArraysCore"]
+git-tree-sha1 = "59ca6eddaaa9849e7de9fd1153b6faf0b1db7b80"
 uuid = "2efcf032-c050-4f8e-a9bb-153293bab1f5"
-version = "0.3.38"
+version = "0.3.42"
 
 [[deps.TOML]]
 deps = ["Dates"]
@@ -1208,9 +1281,9 @@ version = "1.0.1"
 
 [[deps.Tables]]
 deps = ["DataAPI", "DataValueInterfaces", "IteratorInterfaceExtensions", "OrderedCollections", "TableTraits"]
-git-tree-sha1 = "598cd7c1f68d1e205689b1c2fe65a9f85846f297"
+git-tree-sha1 = "f2c1efbc8f3a609aadf318094f8fc5204bdaf344"
 uuid = "bd369af6-aec1-5ad0-b16a-f7cc5008161c"
-version = "1.12.0"
+version = "1.12.1"
 
 [[deps.Tar]]
 deps = ["ArgTools", "SHA"]
@@ -1219,21 +1292,21 @@ version = "1.10.0"
 
 [[deps.TestEnv]]
 deps = ["Pkg"]
-git-tree-sha1 = "2a57e05cb9854e7260c354f1bcdbe5190adba19f"
+git-tree-sha1 = "aec63ef091b11d67040b8b35d2dcdfdc4567c4d0"
 uuid = "1e6cf692-eddd-4d53-88a5-2d735e33781b"
-version = "1.102.0"
+version = "1.102.2"
 
 [[deps.ThreadingUtilities]]
 deps = ["ManualMemory"]
-git-tree-sha1 = "eda08f7e9818eb53661b3deb74e3159460dfbc27"
+git-tree-sha1 = "d969183d3d244b6c33796b5ed01ab97328f2db85"
 uuid = "8290d209-cae3-49c0-8002-c8c24d57dab5"
-version = "0.5.2"
+version = "0.5.5"
 
 [[deps.TimerOutputs]]
 deps = ["ExprTools", "Printf"]
-git-tree-sha1 = "f57facfd1be61c42321765d3551b3df50f7e09f6"
+git-tree-sha1 = "3748bd928e68c7c346b52125cf41fff0de6937d0"
 uuid = "a759f4b9-e2f1-59dc-863e-4aeb61b1ea8f"
-version = "0.5.28"
+version = "0.5.29"
 
     [deps.TimerOutputs.extensions]
     FlameGraphsExt = "FlameGraphs"
@@ -1279,6 +1352,12 @@ git-tree-sha1 = "752ff27037088b747d3138c828ffc0968d2e7766"
 uuid = "19641d66-a62d-11e8-2441-8f57a969a9c4"
 version = "0.5.0"
 
+[[deps.YAML]]
+deps = ["Base64", "Dates", "Printf", "StringEncodings"]
+git-tree-sha1 = "2f58ac39f64b41fb812340347525be3b590cce3b"
+uuid = "ddb6d928-2868-570f-bddf-ab3f9cf99eb6"
+version = "0.4.14"
+
 [[deps.Zlib_jll]]
 deps = ["Libdl"]
 uuid = "83775a58-1f1d-513f-b197-d71354ab007a"
diff --git a/NEWS.md b/NEWS.md
index fdab2a30..fac78b4d 100644
--- a/NEWS.md
+++ b/NEWS.md
@@ -1,3 +1,35 @@
+## VortexStepMethod v2.0.1 2025-08-08
+### Changed
+#### 1. Core New Functionality: YAML Geometry Support
+- **New file:** `yaml_geometry.jl` (290+ lines) — Complete YAML-based wing geometry loading.
+- **New structs:** `WingSectionData`, `WingAirfoilData`, `WingAirfoilInfo` (with `@with_kw` macros).
+- **New function:** `load_polar_data()` — Robust CSV polar data loading with error handling.
+- **New constructors:**
+    - `Wing(geometry_file::String)` — Create wings from YAML files.
+    - `Wing(settings::VSMSettings)` — Create wings from settings.
+
+#### 2. Enhanced Settings System
+- Renamed `vs()` to `VSMSettings()` constructor.
+- Added convenience `Solver(body_aero, settings)` constructor.
+- Improved settings structure and validation.
+
+#### 3. Comprehensive Test Infrastructure
+- **Split tests:** Reorganized from monolithic files to modular structure (`test/module_name/test_*.jl`).
+- **New test module:** `yaml_geometry` with `test_load_polar_data.jl` and `test_wing_constructor.jl`.
+- **Test utilities:** `test_data_utils.jl` with shared helper functions.
+- **Test data:** Extensive YAML and CSV test files in `data`.
+
+#### 4. Data and Examples
+- **New data sets:** Complete `TUDELFT_V3_KITE` with CFD polars and literature results.
+- **Enhanced examples:** Updated examples to use YAML geometry (e.g., `pyramid_model.jl`, `V3_kite.jl`).
+- **Real-world configs:** Production-ready YAML geometry files for various kite configurations.
+
+#### 5. Core Module Improvements
+- **Path handling:** Robust file path resolution for relative/absolute paths.
+- **Error handling:** Comprehensive validation and graceful fallback to INVISCID mode.
+- **Memory management:** Improved file I/O and cleanup in tests.
+- **Documentation:** Added comprehensive docstrings and examples.
+
 ## VortexStepMethod v2.0.0 2025-07-11
 ### Changed
 - bump Interpolations to 0.16
diff --git a/Project.toml b/Project.toml
index df34eed9..7f2dd4db 100644
--- a/Project.toml
+++ b/Project.toml
@@ -23,6 +23,7 @@ SciMLBase = "0bca4576-84f4-4d90-8ffe-ffa030f20462"
 Serialization = "9e88b42a-f829-5b0c-bbe9-9e923198166b"
 StaticArrays = "90137ffa-7385-5640-81b9-e52037218182"
 Statistics = "10745b16-79ce-11e8-11f9-7d13ad32a3b2"
+StructMapping = "7c3b921d-20d6-4eba-ad57-605525e86ab2"
 Timers = "21f18d07-b854-4dab-86f0-c15a3821819a"
 Xfoil = "19641d66-a62d-11e8-2441-8f57a969a9c4"
 YAML = "ddb6d928-2868-570f-bddf-ab3f9cf99eb6"
@@ -55,10 +56,12 @@ Parameters = "0.12"
 Pkg = "1"
 PreallocationTools = "0.4.25"
 PrecompileTools = "1.2.1"
+Random = "1.10.0"
 SciMLBase = "2.77.0"
 Serialization = "1"
 StaticArrays = "1"
 Statistics = "1"
+StructMapping = "0.2.3"
 Test = "1"
 Timers = "0.1"
 Xfoil = "0.5"
@@ -72,7 +75,8 @@ CSV = "336ed68f-0bac-5ca0-87d4-7b16caf5d00b"
 ControlPlots = "23c2ee80-7a9e-4350-b264-8e670f12517c"
 DataFrames = "a93c6f00-e57d-5684-b7b6-d8193f3e46c0"
 Documenter = "e30172f5-a6a5-5a46-863b-614d45cd2de4"
+Random = "9a3f8284-a2c9-5f02-9a11-845980a1fd5c"
 Test = "8dfed614-e22c-5e08-85e1-65c5234f0b40"
 
 [targets]
-test = ["Test", "DataFrames", "CSV", "Documenter", "BenchmarkTools", "ControlPlots", "Aqua"]
+test = ["Test", "DataFrames", "CSV", "Documenter", "BenchmarkTools", "ControlPlots", "Aqua", "Random"]
diff --git a/data/TUDELFT_V3_KITE/literature_results/CFD_RANS_Rey_10e5_Poland2025_alpha_sweep_beta_0.csv b/data/TUDELFT_V3_KITE/literature_results/CFD_RANS_Rey_10e5_Poland2025_alpha_sweep_beta_0.csv
new file mode 100644
index 00000000..f619300f
--- /dev/null
+++ b/data/TUDELFT_V3_KITE/literature_results/CFD_RANS_Rey_10e5_Poland2025_alpha_sweep_beta_0.csv
@@ -0,0 +1,9 @@
+alpha,beta,CL,CD,CS,CMy
+1.02,0,0.2278625272194466,0.0490919571607997,-0.028991478200473,-0.0971304889257096
+4.02,0,0.4610104802890269,0.0516566817024969,-0.06116291297791359,-0.177995425157634
+7.02,0,0.6748642166054709,0.0643789856608573,-0.09170612013580448,-0.2399628564061313
+10.02,0,0.8685945393341531,0.0841781647387978,-0.12014981939630065,-0.2873743657009342
+13.02,0,1.042518829707241,0.1099699784207837,-0.14632493718395287,-0.3234126609849657
+15.02,0,1.147266423064987,0.1293063892392999,-0.16260131332214534,-0.3422906659660041
+17.02,0,1.248363457881334,0.1505397278170317,-0.17819835351371366,-0.3593648645427019
+19.02,0,1.340909392696446,0.172443901716702,-0.19275273990602687,-0.3729793258363525
diff --git a/data/TUDELFT_V3_KITE/literature_results/CFD_RANS_Rey_5e5_Poland2025_alpha_sweep_beta_0_NoStruts.csv b/data/TUDELFT_V3_KITE/literature_results/CFD_RANS_Rey_5e5_Poland2025_alpha_sweep_beta_0_NoStruts.csv
new file mode 100644
index 00000000..eed0a9c8
--- /dev/null
+++ b/data/TUDELFT_V3_KITE/literature_results/CFD_RANS_Rey_5e5_Poland2025_alpha_sweep_beta_0_NoStruts.csv
@@ -0,0 +1,19 @@
+CL,CD,alpha,CS
+-0.133333333,0.0728,-3.98,0
+-0.066666667,0.0672,-2.98,0
+0.073015873,0.0552,-0.98,0
+0.225396825,0.051,1.02,0
+0.384126984,0.052,3.02,0
+0.46031746,0.0536,4.02,0
+0.536507937,0.06,5.02,0
+0.673015873,0.07,7.02,0
+0.803174603,0.075,9.02,0
+0.873015873,0.085,10.02,0
+0.93015873,0.09,11.02,0
+1.041269841,0.115,13.02,0
+1.146031746,0.135,15.02,0
+1.24,0.151,17.02,0
+1.342857143,0.171,19.02,0
+0.88,0.31,21.02,0
+0.91,0.34,23.02,0
+0.93,0.38,25.02,0
diff --git a/data/TUDELFT_V3_KITE/literature_results/Python_VSM_Rey_5e5_Poland2025_alpha_sweep_beta_0.csv b/data/TUDELFT_V3_KITE/literature_results/Python_VSM_Rey_5e5_Poland2025_alpha_sweep_beta_0.csv
new file mode 100644
index 00000000..65726bed
--- /dev/null
+++ b/data/TUDELFT_V3_KITE/literature_results/Python_VSM_Rey_5e5_Poland2025_alpha_sweep_beta_0.csv
@@ -0,0 +1,39 @@
+alpha,CL,CD,CL/CD,CS
+-12.0,-0.2382871512913027,0.10555351086138359,-2.2575009523295666,8.493387378390686e-14
+-11.0,-0.23078413996904473,0.10186112684362705,-2.265674326608765,6.616874649497016e-14
+-10.0,-0.22230140038021914,0.09806363640487119,-2.266909616347621,4.373272668096159e-14
+-9.0,-0.21585315982172304,0.0931590398953698,-2.317039334713575,2.739682786368477e-14
+-8.0,-0.20625706590216833,0.08814998331707347,-2.339842370250558,1.1046588689401156e-14
+-7.0,-0.1998343140258721,0.08290261953105998,-2.410470442987666,-2.389661935808156e-14
+-6.0,-0.18199775713691974,0.07765158375393942,-2.343773923705537,-3.872611350474041e-14
+-5.0,-0.14850648581010087,0.07109437185188841,-2.0888641666246923,-3.2393754503524565e-14
+-4.0,-0.10858858872468641,0.06522454108866148,-1.6648425103839215,-3.0271060429342046e-14
+-3.0,-0.06288342322853809,0.06000714503007155,-1.0479322620168838,-2.895668145826433e-14
+-2.0,-0.007429949914950523,0.055498453779690086,-0.13387670122207165,-3.2169539191587655e-14
+-1.0,0.05656004203302359,0.05159811771021331,1.0961648320327801,-3.44716398526909e-14
+0.0,0.12392449645064037,0.04839062569141725,2.5609194896733913,-3.597944298611074e-14
+1.0,0.19309362003485317,0.04593968204080192,4.203198878550238,-3.699581064093612e-14
+2.0,0.2625331911314792,0.044328371503610776,5.922464151657241,-3.6349856219703554e-14
+3.0,0.3323792213186091,0.04356996032047687,7.628632637574346,-3.6413469417385087e-14
+4.0,0.40297413442239444,0.04359394940688724,9.243808829092464,-3.773253515649088e-14
+5.0,0.4734826904404322,0.04438413803893367,10.667835658430365,-3.826806223929053e-14
+6.0,0.5430144326845379,0.04590240400649957,11.829760214903983,-4.0253505670851383e-14
+7.0,0.610689137470121,0.04806877475261435,12.704487281255428,-4.406262078692334e-14
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+9.0,0.7383699770457292,0.054242295408895566,13.612439729544315,-5.20455622927876e-14
+10.0,0.7982179068869607,0.05807229829781809,13.74524395079696,-5.5385868816441935e-14
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+12.0,0.8988323082495834,0.0690977304744752,13.008130687904623,-6.141415623852904e-14
+13.0,0.9147135983203839,0.08124056010481986,11.259321663220728,6.491282774779828e-13
+14.0,0.9112748609115651,0.0966853408597458,9.425160554933385,4.54748749597064e-13
+15.0,0.9085348699441353,0.11140779158846578,8.155038862095148,3.3836985824286487e-13
+16.0,0.9062580847970818,0.1257712798490804,7.2056043787146695,2.6754981159878576e-13
+17.0,0.8882638215990443,0.13985252773614038,6.3514320118327126,4.0927876403191203e-13
+18.0,0.8801641114980264,0.15426592918480644,5.7054990440800015,2.5988028226070375e-13
+19.0,0.8799535802082414,0.16798064710830107,5.238422373982847,1.821903726884496e-13
+20.0,0.8812698509369349,0.18370556270697425,4.797186530179459,1.3007693874618696e-13
+21.0,0.871379428960392,0.198621428734149,4.387137050185641,5.975307998613411e-15
+22.0,0.8680573492907033,0.21572711063981947,4.023867685040394,-1.822880946847326e-15
+23.0,0.8639910136639356,0.23075669712075686,3.7441644140529626,-5.408316146275571e-16
+24.0,0.8613474653095494,0.24594284553183446,3.5022261511488364,-4.729369019706576e-15
+25.0,0.8583553232582976,0.2571571564052344,3.3378628666498424,-7.613518753563846e-15
diff --git a/data/TUDELFT_V3_KITE/literature_results/Python_VSM_Rey_5e5_n36_CFD_PCHIP_polars_alpha_sweep.csv b/data/TUDELFT_V3_KITE/literature_results/Python_VSM_Rey_5e5_n36_CFD_PCHIP_polars_alpha_sweep.csv
new file mode 100644
index 00000000..b6f0c626
--- /dev/null
+++ b/data/TUDELFT_V3_KITE/literature_results/Python_VSM_Rey_5e5_n36_CFD_PCHIP_polars_alpha_sweep.csv
@@ -0,0 +1,63 @@
+alpha,CL,CD,CS,CMx,CMy,CMz
+-5.0,-0.016639150841432696,0.06461257742824286,8.478187720501367e-17,-3.061887882386819e-16,0.28227103088648064,3.1640606750175953e-17
+-4.508196721311475,-0.15116141710337438,0.06813042331168648,1.6558287946512188e-16,-4.3472875316127167e-16,0.2448193040108129,2.741773931281523e-17
+-4.016393442622951,-0.12359435503424275,0.06467079023399522,2.22928996914706e-16,-5.896358903756748e-16,0.24394876629214812,1.3945762219966873e-17
+-3.5245901639344264,-0.0955075625757297,0.06140805998980694,2.3960563519741807e-16,-6.054561937507627e-16,0.2420546192298006,1.9095600558211657e-17
+-3.0327868852459017,-0.08614032786011963,0.059727576261926124,2.560670910506758e-16,-6.24901983315975e-16,0.24100968398007022,2.597578457810669e-17
+-2.540983606557377,-0.0552050539665637,0.05704706679467209,3.208907979237986e-16,-8.223261858509271e-16,0.23846691212426813,3.934476490419015e-17
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diff --git a/data/TUDELFT_V3_KITE/literature_results/WindTunnel_Re_5e5_Poland2025_alpha_sweep_beta_0.csv b/data/TUDELFT_V3_KITE/literature_results/WindTunnel_Re_5e5_Poland2025_alpha_sweep_beta_0.csv
new file mode 100644
index 00000000..b2a2be53
--- /dev/null
+++ b/data/TUDELFT_V3_KITE/literature_results/WindTunnel_Re_5e5_Poland2025_alpha_sweep_beta_0.csv
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diff --git a/data/TUDELFT_V3_KITE/polars_CFD/1.csv b/data/TUDELFT_V3_KITE/polars_CFD/1.csv
new file mode 100644
index 00000000..8e996699
--- /dev/null
+++ b/data/TUDELFT_V3_KITE/polars_CFD/1.csv
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diff --git a/data/TUDELFT_V3_KITE/polars_CFD/10.csv b/data/TUDELFT_V3_KITE/polars_CFD/10.csv
new file mode 100644
index 00000000..f2572032
--- /dev/null
+++ b/data/TUDELFT_V3_KITE/polars_CFD/10.csv
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diff --git a/data/TUDELFT_V3_KITE/polars_CFD/11.csv b/data/TUDELFT_V3_KITE/polars_CFD/11.csv
new file mode 100644
index 00000000..7ce76468
--- /dev/null
+++ b/data/TUDELFT_V3_KITE/polars_CFD/11.csv
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diff --git a/data/TUDELFT_V3_KITE/polars_CFD/12.csv b/data/TUDELFT_V3_KITE/polars_CFD/12.csv
new file mode 100644
index 00000000..e7290fc8
--- /dev/null
+++ b/data/TUDELFT_V3_KITE/polars_CFD/12.csv
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diff --git a/data/TUDELFT_V3_KITE/polars_CFD/13.csv b/data/TUDELFT_V3_KITE/polars_CFD/13.csv
new file mode 100644
index 00000000..551a1596
--- /dev/null
+++ b/data/TUDELFT_V3_KITE/polars_CFD/13.csv
@@ -0,0 +1,71 @@
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diff --git a/data/TUDELFT_V3_KITE/polars_CFD/14.csv b/data/TUDELFT_V3_KITE/polars_CFD/14.csv
new file mode 100644
index 00000000..c6677eba
--- /dev/null
+++ b/data/TUDELFT_V3_KITE/polars_CFD/14.csv
@@ -0,0 +1,71 @@
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diff --git a/data/TUDELFT_V3_KITE/polars_CFD/15.csv b/data/TUDELFT_V3_KITE/polars_CFD/15.csv
new file mode 100644
index 00000000..d7918746
--- /dev/null
+++ b/data/TUDELFT_V3_KITE/polars_CFD/15.csv
@@ -0,0 +1,71 @@
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diff --git a/data/TUDELFT_V3_KITE/polars_CFD/16.csv b/data/TUDELFT_V3_KITE/polars_CFD/16.csv
new file mode 100644
index 00000000..3a50134a
--- /dev/null
+++ b/data/TUDELFT_V3_KITE/polars_CFD/16.csv
@@ -0,0 +1,71 @@
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diff --git a/data/TUDELFT_V3_KITE/polars_CFD/17.csv b/data/TUDELFT_V3_KITE/polars_CFD/17.csv
new file mode 100644
index 00000000..48e40937
--- /dev/null
+++ b/data/TUDELFT_V3_KITE/polars_CFD/17.csv
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diff --git a/data/TUDELFT_V3_KITE/polars_CFD/18.csv b/data/TUDELFT_V3_KITE/polars_CFD/18.csv
new file mode 100644
index 00000000..1006dc7e
--- /dev/null
+++ b/data/TUDELFT_V3_KITE/polars_CFD/18.csv
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diff --git a/data/TUDELFT_V3_KITE/polars_CFD/19.csv b/data/TUDELFT_V3_KITE/polars_CFD/19.csv
new file mode 100644
index 00000000..3dff7559
--- /dev/null
+++ b/data/TUDELFT_V3_KITE/polars_CFD/19.csv
@@ -0,0 +1,71 @@
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diff --git a/data/TUDELFT_V3_KITE/polars_CFD/2.csv b/data/TUDELFT_V3_KITE/polars_CFD/2.csv
new file mode 100644
index 00000000..4905b021
--- /dev/null
+++ b/data/TUDELFT_V3_KITE/polars_CFD/2.csv
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diff --git a/data/TUDELFT_V3_KITE/polars_CFD/3.csv b/data/TUDELFT_V3_KITE/polars_CFD/3.csv
new file mode 100644
index 00000000..19ad454e
--- /dev/null
+++ b/data/TUDELFT_V3_KITE/polars_CFD/3.csv
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diff --git a/data/TUDELFT_V3_KITE/polars_CFD/4.csv b/data/TUDELFT_V3_KITE/polars_CFD/4.csv
new file mode 100644
index 00000000..b82a2df1
--- /dev/null
+++ b/data/TUDELFT_V3_KITE/polars_CFD/4.csv
@@ -0,0 +1,71 @@
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diff --git a/data/TUDELFT_V3_KITE/polars_CFD/5.csv b/data/TUDELFT_V3_KITE/polars_CFD/5.csv
new file mode 100644
index 00000000..c87f9b7e
--- /dev/null
+++ b/data/TUDELFT_V3_KITE/polars_CFD/5.csv
@@ -0,0 +1,71 @@
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diff --git a/data/TUDELFT_V3_KITE/polars_CFD/6.csv b/data/TUDELFT_V3_KITE/polars_CFD/6.csv
new file mode 100644
index 00000000..b78dbb55
--- /dev/null
+++ b/data/TUDELFT_V3_KITE/polars_CFD/6.csv
@@ -0,0 +1,71 @@
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diff --git a/data/TUDELFT_V3_KITE/polars_CFD/7.csv b/data/TUDELFT_V3_KITE/polars_CFD/7.csv
new file mode 100644
index 00000000..bc35e978
--- /dev/null
+++ b/data/TUDELFT_V3_KITE/polars_CFD/7.csv
@@ -0,0 +1,71 @@
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diff --git a/data/TUDELFT_V3_KITE/polars_CFD/8.csv b/data/TUDELFT_V3_KITE/polars_CFD/8.csv
new file mode 100644
index 00000000..75c8a67b
--- /dev/null
+++ b/data/TUDELFT_V3_KITE/polars_CFD/8.csv
@@ -0,0 +1,71 @@
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diff --git a/data/TUDELFT_V3_KITE/polars_CFD/9.csv b/data/TUDELFT_V3_KITE/polars_CFD/9.csv
new file mode 100644
index 00000000..75c79256
--- /dev/null
+++ b/data/TUDELFT_V3_KITE/polars_CFD/9.csv
@@ -0,0 +1,71 @@
+alpha,Cd,Cs,Cl,Cm
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diff --git a/data/TUDELFT_V3_KITE/vsm_settings.yaml b/data/TUDELFT_V3_KITE/vsm_settings.yaml
new file mode 100644
index 00000000..4e6fda6d
--- /dev/null
+++ b/data/TUDELFT_V3_KITE/vsm_settings.yaml
@@ -0,0 +1,80 @@
+# =============================================================================
+# VSM Settings Configuration File
+# =============================================================================
+#
+# This YAML file configures the Vortex Step Method (VSM) aerodynamic solver
+# for wing analysis. All simulation parameters are centralized here.
+#
+# FILE STRUCTURE:
+# ├── condition:          Flight conditions (wind speed, angles, rates)
+# ├── wings:              Wing geometry and discretization settings
+# └── solver_settings:    Numerical solver parameters and convergence criteria
+#
+# AERODYNAMIC MODELS:
+#   VSM: Vortex Step Method - Full 3D potential flow with wake modeling
+#   LLT: Lifting Line Theory - Classical 1D approach for high aspect ratios
+#
+# PANEL DISTRIBUTIONS:
+#   LINEAR:             Uniform panel spacing along wingspan
+#   COSINE:             Cosine clustering (more panels at tips)
+#   COSINE_VAN_GARREL:  Van Garrel's modified cosine distribution
+#   SPLIT_PROVIDED:     Use predefined section splits from geometry
+#   UNCHANGED:          Preserve original geometry discretization
+#
+# INITIAL CIRCULATION DISTRIBUTIONS:
+#   ELLIPTIC:           Elliptical distribution (optimal for efficiency)
+#   ZEROS:              Start with zero circulation (cold start)
+#
+# SOLVER TYPES:
+#   LOOP:               Iterative fixed-point solver
+#   NEWTON:             Newton-Raphson nonlinear solver
+#
+# USAGE NOTES:
+# - n_panels should be divisible by n_groups for proper load balancing
+# - Higher n_panels improves accuracy but increases computation time
+# - Lower relaxation_factor if convergence issues occur
+
+# Define the flight state for the aerodynamic analysis
+condition:
+    wind_speed: 10.0     # [m/s] Free stream velocity magnitude
+    alpha: 5.0           # [°] Angle of attack (pitch angle relative to flow)
+    beta: 0.0            # [°] Sideslip angle (yaw angle relative to flow)
+    yaw_rate: 0.0        # [°/s] Yaw rate (for dynamic analysis, 0 for static)
+
+# Define wing geometry files and discretization parameters
+wings:
+    - name: V3_Kite                    # Wing identifier for output labeling
+      geometry_file: data/TUDELFT_V3_KITE/wing_geometry_polars_CFD.yaml
+      n_panels: 36                     # Total number of panels along wingspan
+      n_groups: 1                      # Number of panel groups (must divide n_panels)
+      spanwise_panel_distribution: LINEAR    # Panel spacing algorithm
+      spanwise_direction: [0.0, 1.0, 0.0]   # Unit vector defining wingspan direction
+      remove_nan: true                 # Remove NaN values from polar data
+
+# Numerical method settings and convergence criteria
+solver_settings:
+    # --- Core Aerodynamic Model ---
+    aerodynamic_model_type: VSM      # VSM=3D vortex method, LLT=lifting line theory
+    solver_type: LOOP                # LOOP=fixed-point iteration, NEWTON=Newton-Raphson
+    
+    # --- Physical Properties ---
+    density: 1.225                   # [kg/m³] Air density (ISA sea level)
+    mu: 1.81e-5                      # [N·s/m²] Dynamic viscosity (ISA sea level)
+    
+    # --- Convergence Control ---
+    max_iterations: 5000             # Maximum solver iterations before timeout
+    rtol: 1e-6                       # Relative tolerance for convergence
+    tol_reference_error: 0.001       # Reference error tolerance
+    relaxation_factor: 0.01          # [0.001-0.1] Under-relaxation for stability
+    
+    # --- Numerical Stability ---
+    artificial_damping: false        # Enable artificial damping for unstable cases
+    k2: 0.1                          # 2nd-order damping coefficient
+    k4: 0.0                          # 4th-order damping coefficient
+    core_radius_fraction: 1e-20      # Vortex core radius (fraction of chord)
+    
+    # --- Initial Conditions ---
+    type_initial_gamma_distribution: ELLIPTIC  # Starting circulation distribution
+    
+    # --- Output Control ---
+    calc_only_f_and_gamma: false     # true=compute only forces & circulation
diff --git a/data/TUDELFT_V3_KITE/wing_geometry_polars_CFD.yaml b/data/TUDELFT_V3_KITE/wing_geometry_polars_CFD.yaml
new file mode 100644
index 00000000..fb1313c8
--- /dev/null
+++ b/data/TUDELFT_V3_KITE/wing_geometry_polars_CFD.yaml
@@ -0,0 +1,233 @@
+wing_sections:
+  # ---------------------------------------------------------------
+  # headers:
+  #   - airfoil_id: integer, unique identifier for the airfoil (matches wing_airfoils)
+  #   - LE_x: x-coordinate of leading edge
+  #   - LE_y: y-coordinate of leading edge
+  #   - LE_z: z-coordinate of leading edge
+  #   - TE_x: x-coordinate of trailing edge
+  #   - TE_y: y-coordinate of trailing edge
+  #   - TE_z: z-coordinate of trailing edge
+  # ---------------------------------------------------------------
+  headers: [airfoil_id, LE_x, LE_y, LE_z, TE_x, TE_y, TE_z]
+  data:
+    - [19, 0.10494809354160103, 4.110425010287237, 8.27069488190273, 0.9322352740642089, 4.136759541813347, 8.276769856483405]
+    - [18, -0.12594856150986303, 4.095312460948618, 8.381752674216157, 0.9480319715306028, 4.119176793915081, 8.387506882641508]
+    - [17, -0.415204088177974, 4.058392218797549, 8.602739816172805, 0.9806642670037444, 4.0661917809302714, 8.604784652851428]
+    - [16, -0.5839406178913704, 4.017404143963288, 8.823136130673557, 1.0133061573517872, 4.0126965083918655, 8.821802062421128]
+    - [15, -0.6731255454312801, 3.9710648600916856, 9.042296994306358, 1.0459407519807051, 3.959304771307195, 9.038711553698102]
+    - [14, -0.7630010692513897, 3.808661454565653, 9.461650307607462, 1.1148900094481449, 3.8099544198423287, 9.462462687618386]
+    - [13, -0.8034346573868656, 3.671721332477886, 9.640208096108445, 1.1590484514963157, 3.676560321852442, 9.644355401152323]
+    - [12, -0.8426236438512831, 3.5037765531662273, 9.793146879047017, 1.2069146554234733, 3.5081098865401383, 9.79813951074277]
+    - [11, -0.9107041725649544, 3.136094612354681, 10.04874447891271, 1.3282999037052468, 3.1343435230977734, 10.046504069372347]
+    - [10, -0.9734084029764644, 2.799119438334862, 10.344239736588595, 1.341651389866222, 2.7979060165852596, 10.342401274552168]
+    - [9, -1.0012604181004636, 2.60606743950073, 10.460915675643339, 1.3470535121521396, 2.607652208222479, 10.4640730423076]
+    - [8, -1.0255704673876633, 2.3933957820040352, 10.539222758944668, 1.3704766336634273, 2.3946575320852, 10.542717092764684]
+    - [7, -1.066808167099677, 1.9597511829533572, 10.648710571788577, 1.4286937460004634, 1.9587427796536303, 10.645858306351975]
+    - [6, -1.102721455861017, 1.5539231291222366, 10.837899390284646, 1.4218476587327253, 1.5529087742581646, 10.834735742551917]
+    - [5, -1.1174483964012778, 1.3372547196154843, 10.903130724885706, 1.4206278262933396, 1.337221665561774, 10.902962868560538]
+    - [4, -1.1290037004055944, 1.111273134975715, 10.922140965756022, 1.4350857915331694, 1.1111744842343718, 10.920881486234418]
+    - [3, -1.1448828836323988, 0.6642030404518473, 10.908203792543517, 1.4733964618305042, 0.6638228115665804, 10.903361447444984]
+    - [2, -1.1544229650457856, 0.22477286325409476, 10.989264150331223, 1.4484005139953104, 0.2247570459738744, 10.989096462216464]
+    - [1, -1.1557911914860979, 0.0, 11.00491618799836, 1.443146003226444, 0.0, 11.004972573823276]
+    - [2, -1.1544229650457856, -0.22477286325409476, 10.989264150331223, 1.4484005139953104, -0.2247570459738744, 10.989096462216464]
+    - [3, -1.1448828836323988, -0.6642030404518473, 10.908203792543517, 1.4733964618305042, -0.6638228115665804, 10.903361447444984]
+    - [4, -1.1290037004055944, -1.111273134975715, 10.922140965756022, 1.4350857915331694, -1.1111744842343718, 10.920881486234418]
+    - [5, -1.1174483964012778, -1.3372547196154843, 10.903130724885706, 1.4206278262933396, -1.337221665561774, 10.902962868560538]
+    - [6, -1.102721455861017, -1.5539231291222366, 10.837899390284646, 1.4218476587327253, -1.5529087742581646, 10.834735742551917]
+    - [7, -1.066808167099677, -1.9597511829533572, 10.648710571788577, 1.4286937460004634, -1.9587427796536303, 10.645858306351975]
+    - [8, -1.0255704673876633, -2.3933957820040352, 10.539222758944668, 1.3704766336634273, -2.3946575320852, 10.542717092764684]
+    - [9, -1.0012604181004636, -2.60606743950073, 10.460915675643339, 1.3470535121521396, -2.607652208222479, 10.4640730423076]
+    - [10, -0.9734084029764644, -2.799119438334862, 10.344239736588595, 1.341651389866222, -2.7979060165852596, 10.342401274552168]
+    - [11, -0.9107041725649544, -3.136094612354681, 10.04874447891271, 1.3282999037052468, -3.1343435230977734, 10.046504069372347]
+    - [12, -0.8426236438512831, -3.5037765531662273, 9.793146879047017, 1.2069146554234733, -3.5081098865401383, 9.79813951074277]
+    - [13, -0.8034346573868656, -3.671721332477886, 9.640208096108445, 1.1590484514963157, -3.676560321852442, 9.644355401152323]
+    - [14, -0.7630010692513897, -3.808661454565653, 9.461650307607462, 1.1148900094481449, -3.8099544198423287, 9.462462687618386]
+    - [15, -0.6731255454312801, -3.9710648600916856, 9.042296994306358, 1.0459407519807051, -3.959304771307195, 9.038711553698102]
+    - [16, -0.5839406178913704, -4.017404143963288, 8.823136130673557, 1.0133061573517872, -4.0126965083918655, 8.821802062421128]
+    - [17, -0.415204088177974, -4.058392218797549, 8.602739816172805, 0.9806642670037444, -4.0661917809302714, 8.604784652851428]
+    - [18, -0.12594856150986303, -4.095312460948618, 8.381752674216157, 0.9480319715306028, -4.119176793915081, 8.387506882641508]
+    - [19, 0.10494809354160103, -4.110425010287237, 8.27069488190273, 0.9322352740642089, -4.136759541813347, 8.276769856483405]
+
+wing_airfoils:
+  # ---------------------------------------------------------------
+  # headers:
+  #   - airfoil_id: integer, unique identifier for the airfoil
+  #   - type: one of [neuralfoil, breukels_regression, masure_regression, polars]
+  #   - info_dict: dictionary with parameters depending on 'type'
+  #
+  # info_dict fields by type:
+  #   - breukels_regression:
+  #       t: Tube diameter non-dimensionalized by chord (required)
+  #       kappa: Maximum camber height/magnitude, non-dimensionalized by chord (required)
+  #   - neuralfoil:
+  #       dat_file_path: Path to airfoil .dat file (x, y columns)
+  #       model_size: NeuralFoil model size (e.g., "xxxlarge")
+  #       xtr_lower: Lower transition location (0=forced, 1=free)
+  #       xtr_upper: Upper transition location
+  #       n_crit: Critical amplification factor (see guidelines below)
+  #         n_crit guidelines:
+  #           Sailplane:           12–14
+  #           Motorglider:         11–13
+  #           Clean wind tunnel:   10–12
+  #           Average wind tunnel: 9   (standard "e^9 method")
+  #           Dirty wind tunnel:   4–8
+  #   - polars:
+  #       csv_file_path: Path to polar CSV file (columns: alpha [rad], cl, cd, cm)
+  #   - masure_regression:
+  #       t, eta, kappa, delta, lamba, phi: Regression parameters
+  #   - inviscid:
+  #       no further data is required 
+  # ---------------------------------------------------------------
+  alpha_range: [-10, 31, 0.5] # [deg], in this range the polars are calculated
+  reynolds: !!float 1e6 # Reynolds number
+  headers: [airfoil_id, type, info_dict]
+  data:
+  # The polars were generated using 2D RANS CFD simulations at Re=5e5
+  # And fitted using PCHIP interpolation 
+  # See --> https://repository.tudelft.nl/record/uuid:865d59fc-ccff-462e-9bac-e81725f1c0c9
+    - [1, polars, {csv_file_path: "polars_CFD/1.csv"}]
+    - [2, polars, {csv_file_path: "polars_CFD/2.csv"}]
+    - [3, polars, {csv_file_path: "polars_CFD/3.csv"}]
+    - [4, polars, {csv_file_path: "polars_CFD/4.csv"}]
+    - [5, polars, {csv_file_path: "polars_CFD/5.csv"}]
+    - [6, polars, {csv_file_path: "polars_CFD/6.csv"}]
+    - [7, polars, {csv_file_path: "polars_CFD/7.csv"}]
+    - [8, polars, {csv_file_path: "polars_CFD/8.csv"}]
+    - [9, polars, {csv_file_path: "polars_CFD/9.csv"}]
+    - [10, polars, {csv_file_path: "polars_CFD/10.csv"}]
+    - [11, polars, {csv_file_path: "polars_CFD/11.csv"}]
+    - [12, polars, {csv_file_path: "polars_CFD/12.csv"}]
+    - [13, polars, {csv_file_path: "polars_CFD/13.csv"}]
+    - [14, polars, {csv_file_path: "polars_CFD/14.csv"}]
+    - [15, polars, {csv_file_path: "polars_CFD/15.csv"}]
+    - [16, polars, {csv_file_path: "polars_CFD/16.csv"}]
+    - [17, polars, {csv_file_path: "polars_CFD/17.csv"}]
+    - [18, polars, {csv_file_path: "polars_CFD/18.csv"}]
+    - [19, polars, {csv_file_path: "polars_CFD/19.csv"}]
+
+
+
+bridle_nodes:
+  # ---------------------------------------------------------------
+  # headers:
+  #   - id: integer, unique identifier for the node
+  #   - x: x-coordinate [m]
+  #   - y: y-coordinate [m]
+  #   - z: z-coordinate [m]
+  #   - type: node type, either 'knot' or 'pulley'
+  # ---------------------------------------------------------------
+  headers: [id, x, y, z, type]
+  data:
+    - [21, -0.67653494, 2.10580567, 7.08413599, knot]
+    - [22, -0.79196791, 1.01882151, 7.57069579, knot]
+    - [23, -0.79196791, -1.01882151, 7.57069579, knot]
+    - [24, -0.67653494, -2.10580567, 7.08413599, knot]
+    - [25, -0.46444477, 0.77505128, 4.23316161, knot]
+    - [26, -0.46444477, -0.77505128, 4.23316161, knot]
+    - [27, 0.54344694, 1.57655435, 5.91086207, knot]
+    - [28, 0.62960591, 0.92728966, 6.64639402, knot]
+    - [29, 0.62960591, -0.92728966, 6.64639402, knot]
+    - [30, 0.54344694, -1.57655435, 5.91086207, knot]
+    - [31, 0.39092886, 0.71221536, 4.26118728, knot]
+    - [32, 0.39092886, -0.71221536, 4.26118728, knot]
+    - [33, 0.30679124, 0.49235914, 3.39885672, pulley]
+    - [34, 0.28625931, 0.0, 3.19030736, knot]
+    - [35, 0.30679124, -0.49235914, 3.39885672, pulley]
+    - [36, 0.13269336, 0.23394851, 1.48060245, knot]
+    - [37, 0.13269336, -0.23394851, 1.48060245, knot]
+
+bridle_lines:
+  # ---------------------------------------------------------------
+  # headers:
+  #   - name: string, line name
+  #   - rest_length: measured rest length [m]
+  #   - diameter: line diameter [m]
+  #   - material: string, material type (e.g., dyneema)
+  #   - density: material density [kg/m^3]
+  # ---------------------------------------------------------------
+  headers: [name, rest_length, diameter, material, density]
+  data:
+  # front lines
+  - [a6, 11.790, 0.002, dyneema,970]
+  - [A5, 2.870, 0.002, dyneema,970]
+  - [A3, 3.450, 0.002, dyneema,970]
+  - [A2, 3.500, 0.002, dyneema,970]
+  - [A1, 3.690, 0.002, dyneema,970]
+  - [AII, 3.250, 0.002, dyneema,970]
+  - [AI, 3.620, 0.002, dyneema,970]
+  - [amain, 3.910, 0.002, dyneema,970]
+  # rear lines
+  - [br1, 4.410, 0.002, dyneema,970]
+  - [br2, 4.170, 0.002, dyneema,970]
+  - [br3, 4.140, 0.002, dyneema,970]
+  - [br5, 3.580, 0.002, dyneema,970]
+  - [br6, 13.560, 0.002, dyneema,970]
+  - [BRI, 2.360, 0.002, dyneema,970]
+  - [BRII, 2.080, 0.002, dyneema,970]
+  - [BR-main-1, .700, 0.002, dyneema,970]
+  - [M-line, 2.410, 0.002, dyneema,970]
+  # - [S, 1.730, 0.002, dyneema,970] # measured
+  # - [Power Tape, 3.330, 0.002, polyester] # measured
+  - [Steering Tape, 1.530, 0.002, dyneema,970] # trying 0.2m smalller
+  - [Power Tape, 2.900, 0.002, dyneema,970] # trying 0.2m smaller
+
+bridle_connections:
+  # ---------------------------------------------------------------
+  # headers:
+  #   - name: string, line name
+  #   - ci: integer, node id (start)
+  #   - cj: integer, node id (end)
+  #   - ck: integer, third node id (only for pulleys, else omitted or 0)
+  # ---------------------------------------------------------------
+  headers: [name, ci, cj, ck]
+  data:
+    # front lines
+    - [a6,1,25,33] #e.g. this is a pulley
+    - [A5,3,21]
+    - [A3,5,21]
+    - [A2,7,22]
+    - [A1,9,22]
+    - [A1,11,23]
+    - [A2,13,23]
+    - [A3,15,24]
+    - [A5,17,24]
+    - [a6,19,26,35]
+    - [AII,21,25]
+    - [AI,22,25]
+    - [AI,23,26]
+    - [AII,24,26]
+    - [amain,25,0]
+    - [amain,26,0]
+    # rear lines
+    - [a6,1,33,25]
+    - [br6,2,33,36]
+    - [br6,2,36,33]
+    - [br5,4,27]
+    - [br3,6,27]
+    - [br2,8,28]
+    - [br1,10,28]
+    - [br1,12,29]
+    - [br2,14,29]
+    - [br3,16,30]
+    - [br5,18,30]
+    - [a6,19,35,26]
+    - [br6,20,35,37]
+    - [br6,20,37,35]
+    - [BRII,27,31]
+    - [BRI,28,31]
+    - [BRI,29,32]
+    - [BRII,30,32]
+    - [BR-main-1,31,33]
+    - [BR-main-1,32,35]
+    - [M-line,33,36,34]
+    - [M-line,33,34,36]
+    - [M-line,35,34,37]
+    - [M-line,35,37,34]
+    - [Steering Tape,36,0]
+    - [Power Tape,34,0]
+    - [Steering Tape,37,0]
+
+
+
+
diff --git a/data/TUDELFT_V3_LEI_KITE/literature_results/V3_CL_CD_RANS_Lebesque_2024_Rey_300e4.csv b/data/TUDELFT_V3_LEI_KITE/literature_results/V3_CL_CD_RANS_Lebesque_2024_Rey_300e4.csv
deleted file mode 100644
index 5bee35d1..00000000
--- a/data/TUDELFT_V3_LEI_KITE/literature_results/V3_CL_CD_RANS_Lebesque_2024_Rey_300e4.csv
+++ /dev/null
@@ -1,19 +0,0 @@
-CL,CD,aoa
--0.114285714,0.0744,-5
--0.050793651,0.068,-4
-0.082539683,0.0552,-2
-0.247619048,0.0512,0
-0.4,0.052,2
-0.46984127,0.0528,3
-0.542857143,0.0576,4
-0.685714286,0.0656,6
-0.80952381,0.0776,8
-0.873015873,0.0832,9
-0.93015873,0.0928,10
-1.047619048,0.1104,12
-1.155555556,0.1296,14
-1.250793651,0.1504,16
-1.13015873,0.2024,18
-1.146031746,0.2248,20
-1.146031746,0.2252,22
-1.158730159,0.2816,24
diff --git a/data/pyramid_model/polars/V3_kite_midspan_airfoil_polar.csv b/data/pyramid_model/polars/V3_kite_midspan_airfoil_polar.csv
new file mode 100644
index 00000000..8e996699
--- /dev/null
+++ b/data/pyramid_model/polars/V3_kite_midspan_airfoil_polar.csv
@@ -0,0 +1,71 @@
+alpha,Cd,Cs,Cl,Cm
+-10.0,0.1759893858334057,2.963819078393553e-21,-0.7493726713784946,0.2323775006207747
+-9.5,0.16289734924603438,2.7877286866584314e-21,-0.6924217529040287,0.2150382675337481
+-9.0,0.1504301874457461,2.6166544368792525e-21,-0.6371323632116463,0.1982607529225381
+-8.5,0.13862765245364775,2.4505707167459407e-21,-0.583498032661642,0.182046261914037
+-8.0,0.1275294962908461,2.2894519139484196e-21,-0.5315122916143107,0.16639609963513724
+-7.5,0.11717547097844788,2.133272416176612e-21,-0.4811686704299467,0.15131157121273117
+-7.0,0.10760532853756002,1.9820066111204418e-21,-0.4324606994688453,0.13679398177371113
+-6.5,0.09885882098928928,1.8356288864698326e-21,-0.38538190909130093,0.12284463644496953
+-6.0,0.09097570035474245,1.694113629914708e-21,-0.3399258296576083,0.10946484035339869
+-5.5,0.08399571865502635,1.557435229144991e-21,-0.2960859915280623,0.09665589862589102
+-5.0,0.0779586279112478,1.4255680718506053e-21,-0.2538559250629577,0.0844191163893389
+-4.5,0.07276768079432067,1.304392579507697e-21,-0.21595504346747285,0.07305505165488536
+-4.0,0.06820918462412777,1.1952100521496464e-21,-0.18295885873231385,0.06261743540439639
+-3.5,0.06414747339522936,1.0911261953022303e-21,-0.15164504939606627,0.05273733222084856
+-3.0,0.06044688110218564,9.852467144912246e-22,-0.11879129399731583,0.0430458066872185
+-2.5,0.056971741739556846,8.706773152424055e-22,-0.08117527107464828,0.03317392338648285
+-2.0,0.0535863893019032,7.405237030815495e-22,-0.0355746591666493,0.0227527469016182
+-1.5,0.050350423572556896,5.856067102929198e-22,0.026226099750827674,0.011481449300827454
+-1.0,0.04735778299115752,4.0923582258582316e-22,0.10429086281980794,-0.00026565530478757544
+-0.5,0.04452430953672641,2.232497256236004e-22,0.189614400178524,-0.011844789267901869
+0.0,0.0417658451882849,3.948710506959264e-23,0.2731914819652083,-0.0226121749411904
+0.5,0.038938158507699175,-1.5308243840478701e-22,0.3557444890017091,-0.03336699893672287
+1.0,0.036117770291757965,-3.560898065690111e-22,0.4410912179803868,-0.0442048470204237
+1.5,0.03355165087186637,-5.435970674210673e-22,0.5248695628452424,-0.05342654027574999
+2.0,0.0314867705794295,-6.896662889589436e-22,0.6027174175402769,-0.0593328997861588
+2.5,0.029737782322488943,-8.01300470612271e-22,0.6754871235581754,-0.06287604536210906
+3.0,0.028000254685969946,-9.031057734401621e-22,0.7466883077319687,-0.06610779561686102
+3.5,0.026342531516603155,-9.955490078848253e-22,0.8159447920161751,-0.06897851983807372
+4.0,0.024832956661119197,-1.07909698438847e-21,0.882880398365313,-0.0714385873134062
+4.5,0.023539873966248726,-1.1542165133933057e-21,0.9471189487339009,-0.07343836733051758
+5.0,0.022531627278722356,-1.221374405341541e-21,1.0082842650764576,-0.07492822917706685
+5.5,0.021876560445270733,-1.2810374706753849e-21,1.0660001693475016,-0.07585854214071311
+6.0,0.0216430173126245,-1.3336725198370469e-21,1.1198904835015508,-0.0761796755091154
+6.5,0.021855502747260325,-1.3836048414175573e-21,1.1730032825989054,-0.07614317006852858
+7.0,0.022476813390075807,-1.4334901652977566e-21,1.2273051287313683,-0.07604692845243605
+7.5,0.023482730749432957,-1.4812909638545697e-21,1.280797574400714,-0.0759108627193397
+8.0,0.02484903633369378,-1.52496970946492e-21,1.3314821721087169,-0.07575488492774146
+8.5,0.026551511651220286,-1.5624888745057316e-21,1.3773604743571508,-0.07559890713614321
+9.0,0.028565938210374484,-1.5918109313539293e-21,1.4164340336477907,-0.07546284140304686
+9.5,0.030868097519518387,-1.610898352386437e-21,1.4467044024824103,-0.07536659978695433
+10.0,0.033433771087014,-1.6177136099801785e-21,1.4661731333627843,-0.0753300943463675
+10.5,0.03772956880131731,-1.6057175342808367e-21,1.4791075252059553,-0.07796780684956318
+11.0,0.04483478356085069,-1.573737170673408e-21,1.4901408957026034,-0.0844740956822261
+11.5,0.054144221388925814,-1.527784314393788e-21,1.4978238255149576,-0.09273868782897009
+12.0,0.0650526883088543,-1.473870760677872e-21,1.5007068953052467,-0.100651310274409
+12.5,0.0813064038148973,-1.376249216669895e-21,1.4478125078785742,-0.10828545090079453
+13.0,0.10393510413553603,-1.227647034548664e-21,1.327791188740308,-0.11661304574760116
+13.5,0.12825887039541226,-1.0767879771019317e-21,1.1986357026030765,-0.12487149403527704
+14.0,0.1495977837191678,-9.723958071174512e-22,1.1183388141795072,-0.1322981949842703
+14.5,0.16758478702300417,-9.126318501956502e-22,1.0836834275674483,-0.13916224193214982
+15.0,0.18464791495839383,-8.633432558691364e-22,1.0549329936239267,-0.14581097523802025
+15.5,0.20029988625288483,-8.247825228239323e-22,1.0353010972003385,-0.15159916465463338
+16.0,0.2140534196340252,-7.972021497460613e-22,1.028001323148079,-0.155881579934741
+16.5,0.22575911507873533,-7.765045354525572e-22,1.0279465928930964,-0.1588574292964903
+17.0,0.23609366837079485,-7.591163461883778e-22,1.0279074596231041,-0.1612711173409803
+17.5,0.24580894194804037,-7.460764817814329e-22,1.0278839558321435,-0.1632952083953905
+18.0,0.2556567982483086,-7.38423842059632e-22,1.0278761140142585,-0.1651022667869003
+18.5,0.265699815399311,-7.344986178163224e-22,1.0281104344749106,-0.16669752709328292
+19.0,0.27558646593010794,-7.316573885898107e-22,1.0287304726554904,-0.16807297439296806
+19.5,0.28544745388056003,-7.294636373254447e-22,1.0296118437539339,-0.1693812987641203
+20.0,0.2954134832905278,-7.274808469685726e-22,1.030630162968177,-0.1707751902849041
+20.5,0.3055500999908466,-7.253401091686849e-22,1.0321158975458387,-0.17232913459444757
+21.0,0.3157783912824044,-7.232601462733436e-22,1.034270073518937,-0.17395281724452416
+21.5,0.32601237341014067,-7.216858872750047e-22,1.036774144262008,-0.17555172818226641
+22.0,0.3361660626189948,-7.210622611661238e-22,1.039309563149587,-0.1770313573548068
+22.5,0.3462258406278082,-7.210927738558214e-22,1.0418506907541978,-0.17838813341813575
+23.0,0.35623515262436534,-7.213063626837044e-22,1.044574269637424,-0.17967706251871235
+23.5,0.36619361005701967,-7.21886103787958e-22,1.0474653261573934,-0.18089150083937203
+24.0,0.3761008243741252,-7.230150733067677e-22,1.0505088866722323,-0.18202480456295017
+24.5,0.38595640702403533,-7.248763473783189e-22,1.0536899775400672,-0.18307032987228236
diff --git a/data/pyramid_model/vsm_settings.yaml b/data/pyramid_model/vsm_settings.yaml
new file mode 100644
index 00000000..93ba2ca8
--- /dev/null
+++ b/data/pyramid_model/vsm_settings.yaml
@@ -0,0 +1,80 @@
+# =============================================================================
+# VSM Settings Configuration File
+# =============================================================================
+#
+# This YAML file configures the Vortex Step Method (VSM) aerodynamic solver
+# for wing analysis. All simulation parameters are centralized here.
+#
+# FILE STRUCTURE:
+# ├── condition:          Flight conditions (wind speed, angles, rates)
+# ├── wings:              Wing geometry and discretization settings
+# └── solver_settings:    Numerical solver parameters and convergence criteria
+#
+# AERODYNAMIC MODELS:
+#   VSM: Vortex Step Method - Full 3D potential flow with wake modeling
+#   LLT: Lifting Line Theory - Classical 1D approach for high aspect ratios
+#
+# PANEL DISTRIBUTIONS:
+#   LINEAR:             Uniform panel spacing along wingspan
+#   COSINE:             Cosine clustering (more panels at tips)
+#   COSINE_VAN_GARREL:  Van Garrel's modified cosine distribution
+#   SPLIT_PROVIDED:     Use predefined section splits from geometry
+#   UNCHANGED:          Preserve original geometry discretization
+#
+# INITIAL CIRCULATION DISTRIBUTIONS:
+#   ELLIPTIC:           Elliptical distribution (optimal for efficiency)
+#   ZEROS:              Start with zero circulation (cold start)
+#
+# SOLVER TYPES:
+#   LOOP:               Iterative fixed-point solver
+#   NEWTON:             Newton-Raphson nonlinear solver
+#
+# USAGE NOTES:
+# - n_panels should be divisible by n_groups for proper load balancing
+# - Higher n_panels improves accuracy but increases computation time
+# - Lower relaxation_factor if convergence issues occur
+
+# Define the flight state for the aerodynamic analysis
+condition:
+    wind_speed: 10.0     # [m/s] Free stream velocity magnitude
+    alpha: 5.0           # [°] Angle of attack (pitch angle relative to flow)
+    beta: 0.0            # [°] Sideslip angle (yaw angle relative to flow)
+    yaw_rate: 0.0        # [°/s] Yaw rate (for dynamic analysis, 0 for static)
+
+# Define wing geometry files and discretization parameters
+wings:
+    - name: V3_Kite                    # Wing identifier for output labeling
+      geometry_file: data/pyramid_model/wing_geometry.yaml
+      n_panels: 2                     # Total number of panels along wingspan
+      n_groups: 1                      # Number of panel groups (must divide n_panels)
+      spanwise_panel_distribution: LINEAR    # Panel spacing algorithm
+      spanwise_direction: [0.0, 1.0, 0.0]   # Unit vector defining wingspan direction
+      remove_nan: true                 # Remove NaN values from polar data
+
+# Numerical method settings and convergence criteria
+solver_settings:
+    # --- Core Aerodynamic Model ---
+    aerodynamic_model_type: VSM      # VSM=3D vortex method, LLT=lifting line theory
+    solver_type: LOOP                # LOOP=fixed-point iteration, NEWTON=Newton-Raphson
+    
+    # --- Physical Properties ---
+    density: 1.225                   # [kg/m³] Air density (ISA sea level)
+    mu: 1.81e-5                      # [N·s/m²] Dynamic viscosity (ISA sea level)
+    
+    # --- Convergence Control ---
+    max_iterations: 5000             # Maximum solver iterations before timeout
+    rtol: 1e-6                       # Relative tolerance for convergence
+    tol_reference_error: 0.001       # Reference error tolerance
+    relaxation_factor: 0.01          # [0.001-0.1] Under-relaxation for stability
+    
+    # --- Numerical Stability ---
+    artificial_damping: false        # Enable artificial damping for unstable cases
+    k2: 0.1                          # 2nd-order damping coefficient
+    k4: 0.0                          # 4th-order damping coefficient
+    core_radius_fraction: 1e-20      # Vortex core radius (fraction of chord)
+    
+    # --- Initial Conditions ---
+    type_initial_gamma_distribution: ELLIPTIC  # Starting circulation distribution
+    
+    # --- Output Control ---
+    calc_only_f_and_gamma: false     # true=compute only forces & circulation
diff --git a/data/pyramid_model/wing_geometry.yaml b/data/pyramid_model/wing_geometry.yaml
new file mode 100644
index 00000000..74e62c61
--- /dev/null
+++ b/data/pyramid_model/wing_geometry.yaml
@@ -0,0 +1,68 @@
+# Kite system geometry for simulation based on provided Julia code
+
+wing_sections:
+  # ---------------------------------------------------------------
+  # headers: [airfoil_id, LE_x, LE_y, LE_z, TE_x, TE_y, TE_z]
+  # airfoil_id: 1 (since only one polar/interpolator is used)
+  # The kite is represented by 4 chordwise points at y = width/2, -width/2 and at y = 0.
+  # Chord positions from get_kite_points(s): P2 (center right), P3 (center left)
+  # Bridle/other points are omitted for simplicity.
+  # Units: meters
+  # ---------------------------------------------------------------
+  headers: [airfoil_id, LE_x, LE_y, LE_z, TE_x, TE_y, TE_z]
+  data:
+    - [1, 0.0,  4.08, 4.9, 2.0,  4.08, 4.9]      # Right tip chord (P2)
+    - [1, 0.0, -4.08, 4.9, 2.0, -4.08, 4.9]      # Left tip chord  (P3)
+    - [1, 0.0, 0.0,   8.05,  2.0, 0.0,   8.05]       # Bridle attachment (P4/P5 merged, approx.)
+
+wing_airfoils:
+  # ---------------------------------------------------------------
+  # Only one polar, which is interpolated in code; you may later link to a CSV file.
+  # ---------------------------------------------------------------
+  alpha_range: [-180, 180, 1] # deg
+  reynolds: 1e6
+  headers: [airfoil_id, type, info_dict]
+  data:
+    - [1, polars, {csv_file_path: "polars/V3_kite_midspan_airfoil_polar.csv"}]
+
+bridle_nodes:
+  # ---------------------------------------------------------------
+  # Use the points from get_kite_points(s), assuming:
+  # - P1: Bridle point
+  # - P2: right tip
+  # - P3: left tip
+  # - P4/P5: at width/2, -width/2, z = bridle height
+  # ---------------------------------------------------------------
+  headers: [id, x, y, z, type]
+  data:
+    - [1, 0.0,     0.0,    0.0,   knot]  # Bridle origin
+    - [2, 0.0,     4.08,   8.05,  knot]  # Right tip
+    - [3, 0.0,    -4.08,   8.05,  knot]  # Left tip
+    - [4, 0.0,     4.08,   4.9,   knot]  # Bridle top right
+    - [5, 0.0,    -4.08,   4.9,   knot]  # Bridle top left
+
+bridle_lines:
+  # ---------------------------------------------------------------
+  headers: [name, rest_length, diameter, material, density]
+  data:
+    - [bridle_main, 33.4, 0.0025, dyneema, 970]
+
+bridle_connections:
+  # ---------------------------------------------------------------
+  # Very simplified; you can expand as needed. Connects bridle origin to tips and bridle tops.
+  # headers: [name, ci, cj, ck]
+  data:
+    - [bridle_main, 1, 2, 0]
+    - [bridle_main, 1, 3, 0]
+    - [bridle_main, 1, 4, 0]
+    - [bridle_main, 1, 5, 0]
+    - [bridle_top, 4, 2, 0]
+    - [bridle_top, 5, 3, 0]
+
+tether:
+  # Tether from bridle origin (node 1) extending for l_tether meters
+  length: 50.0
+  diameter: 0.004
+  material: dyneema
+  density: 724.0
+  segments: 14
diff --git a/data/ram_air_kite_body.obj b/data/ram_air_kite/ram_air_kite_body.obj
similarity index 100%
rename from data/ram_air_kite_body.obj
rename to data/ram_air_kite/ram_air_kite_body.obj
diff --git a/data/ram_air_kite_foil.dat b/data/ram_air_kite/ram_air_kite_foil.dat
similarity index 100%
rename from data/ram_air_kite_foil.dat
rename to data/ram_air_kite/ram_air_kite_foil.dat
diff --git a/data/ram_air_kite_foil_cd_polar.csv b/data/ram_air_kite/ram_air_kite_foil_cd_polar.csv
similarity index 100%
rename from data/ram_air_kite_foil_cd_polar.csv
rename to data/ram_air_kite/ram_air_kite_foil_cd_polar.csv
diff --git a/data/ram_air_kite_foil_cl_polar.csv b/data/ram_air_kite/ram_air_kite_foil_cl_polar.csv
similarity index 100%
rename from data/ram_air_kite_foil_cl_polar.csv
rename to data/ram_air_kite/ram_air_kite_foil_cl_polar.csv
diff --git a/data/ram_air_kite_foil_cm_polar.csv b/data/ram_air_kite/ram_air_kite_foil_cm_polar.csv
similarity index 100%
rename from data/ram_air_kite_foil_cm_polar.csv
rename to data/ram_air_kite/ram_air_kite_foil_cm_polar.csv
diff --git a/data/vsm_settings.yaml b/data/ram_air_kite/vsm_settings.yaml
similarity index 100%
rename from data/vsm_settings.yaml
rename to data/ram_air_kite/vsm_settings.yaml
diff --git a/data/vsm_settings_dual.yaml b/data/ram_air_kite/vsm_settings_dual.yaml
similarity index 100%
rename from data/vsm_settings_dual.yaml
rename to data/ram_air_kite/vsm_settings_dual.yaml
diff --git a/examples/V3_kite.jl b/examples/V3_kite.jl
new file mode 100644
index 00000000..9f50b6d4
--- /dev/null
+++ b/examples/V3_kite.jl
@@ -0,0 +1,90 @@
+using LinearAlgebra
+using VortexStepMethod
+using ControlPlots
+
+project_dir = dirname(dirname(pathof(VortexStepMethod)))  # Go up one level from src to project root#
+literature_paths = [
+    joinpath(project_dir, "data", "TUDELFT_V3_KITE", "literature_results","CFD_RANS_Rey_5e5_Poland2025_alpha_sweep_beta_0_NoStruts.csv"),
+    joinpath(project_dir, "data", "TUDELFT_V3_KITE", "literature_results","CFD_RANS_Rey_10e5_Poland2025_alpha_sweep_beta_0.csv"),
+    joinpath(project_dir, "data", "TUDELFT_V3_KITE", "literature_results","Python_VSM_Rey_5e5_n36_CFD_PCHIP_polars_alpha_sweep.csv"),
+    joinpath(project_dir, "data", "TUDELFT_V3_KITE", "literature_results","WindTunnel_Re_5e5_Poland2025_alpha_sweep_beta_0.csv"),
+    ]
+labels= [
+    "Julia VSM 2D CFD PCHIP",
+    "CFD RANS Re=5e5", 
+    "CFD RANS Re=10e5 (With Struts)", 
+    "Python VSM 2D CFD PCHIP Re=5e5",
+    "Wind Tunnel Re=5e5 (With Struts)"
+    ]
+
+# Load VSM settings from YAML configuration file
+settings = VSMSettings("TUDELFT_V3_KITE/vsm_settings.yaml")
+
+# Create wing, body_aero, and solver objects using settings
+wing = Wing(settings)
+body_aero = BodyAerodynamics([wing])
+solver = Solver(body_aero, settings)
+
+# Set flight conditions from settings
+set_va!(body_aero, settings)
+
+# Extract values for plotting (optional - for reference)
+wind_speed = settings.condition.wind_speed
+angle_of_attack_deg = settings.condition.alpha
+sideslip_deg = settings.condition.beta
+yaw_rate = settings.condition.yaw_rate
+
+# Using plotting modules, to create more comprehensive plots
+PLOT = true
+USE_TEX = false
+
+# Plotting polars
+PLOT && plot_polars(
+    [solver],
+    [body_aero],
+    labels,
+    literature_path_list=literature_paths,
+    angle_range=range(-5, 25, length=30),
+    angle_type="angle_of_attack",
+    angle_of_attack=angle_of_attack_deg,
+    side_slip=sideslip_deg,
+    v_a=wind_speed,
+    title="$(wing.n_panels)_panels_$(wing.spanwise_distribution)_from_yaml_settings",
+    data_type=".pdf",
+    is_save=false,
+    is_show=true,
+    use_tex=USE_TEX
+)
+
+
+# Plotting geometry
+results = VortexStepMethod.solve(solver, body_aero; log=true)
+PLOT && plot_geometry(
+    body_aero,
+    "";
+    data_type=".svg",
+    save_path="",
+    is_save=false,
+    is_show=true,
+    view_elevation=15,
+    view_azimuth=-120,
+    use_tex=USE_TEX
+)
+
+
+# Plotting spanwise distributions
+body_y_coordinates = [panel.aero_center[2] for panel in body_aero.panels]
+
+PLOT && plot_distribution(
+    [body_y_coordinates],
+    [results],
+    ["VSM"];
+    title="CAD_spanwise_distributions_alpha_$(round(angle_of_attack_deg, digits=1))_delta_$(round(sideslip_deg, digits=1))_yaw_$(round(yaw_rate, digits=1))_v_a_$(round(wind_speed, digits=1))",
+    data_type=".pdf",
+    is_save=false,
+    is_show=true,
+    use_tex=USE_TEX
+)
+
+
+nothing
\ No newline at end of file
diff --git a/examples/bench.jl b/examples/bench.jl
index 87332aec..89544278 100644
--- a/examples/bench.jl
+++ b/examples/bench.jl
@@ -56,7 +56,11 @@ println("Rectangular wing, solve:")
 @time solve(vsm_solver, body_aero, nothing)
 
 # Create wing geometry
-wing = RamAirWing("data/ram_air_kite_body.obj", "data/ram_air_kite_foil.dat"; prn=false)
+wing = RamAirWing(
+    joinpath("data", "ram_air_kite", "ram_air_kite_body.obj"), 
+    joinpath("data", "ram_air_kite", "ram_air_kite_foil.dat"); 
+    prn=false
+)
 body_aero = BodyAerodynamics([wing])
 
 # Create solvers
diff --git a/examples/cleanup.jl b/examples/cleanup.jl
index ce0d248d..c1d8f1cc 100644
--- a/examples/cleanup.jl
+++ b/examples/cleanup.jl
@@ -2,9 +2,9 @@
 # delete the generated polars
 # it is useful if you want to benchmark the polar generation or if you have changed parameters
 
-file1="data/ram_air_kite_foil_cl_polar.csv"
-file2="data/ram_air_kite_foil_cd_polar.csv"
-file3="data/ram_air_kite_foil_cm_polar.csv"
+file1="data/ram_air_kite/ram_air_kite_foil_cl_polar.csv"
+file2="data/ram_air_kite/ram_air_kite_foil_cd_polar.csv"
+file3="data/ram_air_kite/ram_air_kite_foil_cm_polar.csv"
 isfile(file1) && rm(file1)
 isfile(file2) && rm(file2)
 isfile(file3) && rm(file3)
diff --git a/examples/menu.jl b/examples/menu.jl
index ee4ba929..4454ccee 100644
--- a/examples/menu.jl
+++ b/examples/menu.jl
@@ -9,7 +9,10 @@ using REPL.TerminalMenus
 
 url = "https://opensourceawe.github.io/VortexStepMethod.jl/dev"
 
-options = ["rectangular_wing = include(\"rectangular_wing.jl\")",
+options = [
+           "V3_kite = include(\"V3_kite.jl\")",
+           "pyramid_model = include(\"pyramid_model.jl\")",
+           "rectangular_wing = include(\"rectangular_wing.jl\")",
            "ram_air_kite = include(\"ram_air_kite.jl\")",
            "stall_model = include(\"stall_model.jl\")",
            "bench = include(\"bench.jl\")",
diff --git a/examples/pyramid_model.jl b/examples/pyramid_model.jl
new file mode 100644
index 00000000..837e26ef
--- /dev/null
+++ b/examples/pyramid_model.jl
@@ -0,0 +1,76 @@
+using LinearAlgebra
+using VortexStepMethod
+using ControlPlots
+
+project_dir = dirname(dirname(pathof(VortexStepMethod)))  # Go up one level from src to project root
+
+# Load VSM vsm_settings from YAML configuration file
+vsm_settings = VSMSettings("pyramid_model/vsm_settings.yaml")
+
+# Create wing, body_aero, and solver objects using vsm_settings
+wing = Wing(vsm_settings)
+body_aero = BodyAerodynamics([wing])
+solver = Solver(body_aero, vsm_settings)
+
+# Set flight conditions from settings
+set_va!(body_aero, vsm_settings)
+
+# Extract values for plotting (optional - for reference)
+wind_speed = vsm_settings.condition.wind_speed
+angle_of_attack_deg = vsm_settings.condition.alpha
+sideslip_deg = vsm_settings.condition.beta
+yaw_rate = vsm_settings.condition.yaw_rate
+
+# Run the solver
+results = VortexStepMethod.solve(solver, body_aero; log=true)
+
+# Using plotting modules, to create more comprehensive plots
+PLOT = true
+USE_TEX = false
+
+# Plotting polars
+PLOT && plot_polars(
+    [solver],
+    [body_aero],
+    ["VSM Pyramid Model"],
+    angle_range=range(-5, 25, length=30),
+    angle_type="angle_of_attack",
+    angle_of_attack=angle_of_attack_deg,
+    side_slip=sideslip_deg,
+    v_a=wind_speed,
+    title="$(wing.n_panels)_panels_$(wing.spanwise_distribution)_pyramid_model",
+    data_type=".pdf",
+    is_save=false,
+    is_show=true,
+    use_tex=USE_TEX
+)
+
+# Plotting geometry
+results = VortexStepMethod.solve(solver, body_aero; log=true)
+PLOT && plot_geometry(
+    body_aero,
+    "";
+    data_type=".svg",
+    save_path="",
+    is_save=false,
+    is_show=true,
+    view_elevation=15,
+    view_azimuth=-120,
+    use_tex=USE_TEX
+)
+
+# Plotting spanwise distributions
+body_y_coordinates = [panel.aero_center[2] for panel in body_aero.panels]
+
+PLOT && plot_distribution(
+    [body_y_coordinates],
+    [results],
+    ["VSM"];
+    title="pyramid_spanwise_distributions_alpha_$(round(angle_of_attack_deg, digits=1))_delta_$(round(sideslip_deg, digits=1))_yaw_$(round(yaw_rate, digits=1))_v_a_$(round(wind_speed, digits=1))",
+    data_type=".pdf",
+    is_save=false,
+    is_show=true,
+    use_tex=USE_TEX
+)
+
+nothing
\ No newline at end of file
diff --git a/examples/ram_air_kite.jl b/examples/ram_air_kite.jl
index ab30b027..f10b8d5b 100644
--- a/examples/ram_air_kite.jl
+++ b/examples/ram_air_kite.jl
@@ -9,7 +9,11 @@ DEFORM = false
 LINEARIZE = false
 
 # Create wing geometry
-wing = RamAirWing("data/ram_air_kite_body.obj", "data/ram_air_kite_foil.dat"; prn=PRN)
+wing = RamAirWing(
+    joinpath("data", "ram_air_kite", "ram_air_kite_body.obj"), 
+    joinpath("data", "ram_air_kite", "ram_air_kite_foil.dat"); 
+    prn=PRN
+)
 body_aero = BodyAerodynamics([wing];)
 println("First init")
 @time VortexStepMethod.reinit!(body_aero)
diff --git a/src/VortexStepMethod.jl b/src/VortexStepMethod.jl
index 15d3829b..c852c48e 100644
--- a/src/VortexStepMethod.jl
+++ b/src/VortexStepMethod.jl
@@ -12,7 +12,7 @@ using LaTeXStrings
 using NonlinearSolve
 import NonlinearSolve: solve!, solve
 using Interpolations
-using Interpolations: Extrapolation
+import Interpolations: Extrapolation
 using Parameters
 using Serialization
 using Timers
@@ -22,10 +22,11 @@ using Pkg
 using DifferentiationInterface
 import SciMLBase: successful_retcode
 import YAML
+using StructMapping
 using Xfoil
 
 # Export public interface
-export VSMSettings, WingSettings, SolverSettings, vs
+export VSMSettings, WingSettings, SolverSettings
 export Wing, Section, RamAirWing, reinit!
 export BodyAerodynamics
 export Solver, solve, solve_base!, solve!, VSMSolution, linearize
@@ -39,14 +40,14 @@ export PanelDistribution, LINEAR, COSINE, COSINE_VAN_GARREL, SPLIT_PROVIDED, UNC
 export InitialGammaDistribution, ELLIPTIC, ZEROS
 export SolverStatus, FEASIBLE, INFEASIBLE, FAILURE
 export SolverType, LOOP, NONLIN
+export load_polar_data
 
-export plot_geometry, plot_distribution, plot_circulation_distribution, plot_geometry, plot_polars, save_plot, show_plot, plot_polar_data
+export plot_geometry, plot_distribution, plot_circulation_distribution, plot_polars, save_plot, show_plot, plot_polar_data
 
 # the following functions are defined in ext/VortexStepMethodExt.jl
 function plot_geometry end
 function plot_distribution end
 function plot_circulation_distribution end
-function plot_geometry end
 function plot_polars end
 function save_plot end
 function show_plot end
@@ -202,7 +203,9 @@ const AeroData = Union{
     }
 
 function menu()
-   Main.include("examples/menu.jl")
+   # Load the examples menu using a portable path
+   ex = joinpath(dirname(pathof(@__MODULE__)), "..", "examples", "menu.jl")
+   Base.include(Main, normpath(ex))
 end
 
 """
@@ -213,11 +216,11 @@ Copy all example scripts to the folder "examples"
 """
 function copy_examples()
     PATH = "examples"
-    if ! isdir(PATH) 
+    if ! isdir(PATH)
         mkdir(PATH)
     end
     src_path = joinpath(dirname(pathof(@__MODULE__)), "..", PATH)
-    copy_files("examples", readdir(src_path))
+    copy_files(PATH, readdir(src_path))
 end
 
 function install_examples(add_packages=true)
@@ -270,6 +273,7 @@ include("settings.jl")
 include("wing_geometry.jl")
 include("polars.jl")
 include("ram_geometry.jl")
+include("yaml_geometry.jl")
 include("filament.jl")
 include("panel.jl")
 include("body_aerodynamics.jl")
diff --git a/src/body_aerodynamics.jl b/src/body_aerodynamics.jl
index 6860ac94..87e75fec 100644
--- a/src/body_aerodynamics.jl
+++ b/src/body_aerodynamics.jl
@@ -18,7 +18,7 @@ Main structure for calculating aerodynamic properties of bodies. Use the constru
 - `work_vectors`::NTuple{10, MVec3} = ntuple(_ -> zeros(MVec3), 10)
 - `AIC::Array{Float64, 3}` = zeros(3, P, P)
 - `projected_area::Float64` = 1.0: The area projected onto the xy-plane of the kite body reference frame [m²]
-- `y::MVector{P, Float64}` = zeros(MVector{P, Float64})
+- `y::MVector{P, Float64}` = MVector{P,Float64}(zeros(P))
 - `cache::Vector{PreallocationTools.LazyBufferCache{typeof(identity), typeof(identity)}}` = [LazyBufferCache() for _ in 1:5]
 """
 @with_kw mutable struct BodyAerodynamics{P}
@@ -26,16 +26,16 @@ Main structure for calculating aerodynamic properties of bodies. Use the constru
     wings::Union{Vector{Wing}, Vector{RamAirWing}}
     _va::MVec3 = zeros(MVec3)
     omega::MVec3 = zeros(MVec3)
-    gamma_distribution::MVector{P, Float64} = zeros(MVector{P, Float64})
-    alpha_uncorrected::MVector{P, Float64} = zeros(MVector{P, Float64})
-    alpha_corrected::MVector{P, Float64} = zeros(MVector{P, Float64})
-    stall_angle_list::MVector{P, Float64} = zeros(MVector{P, Float64})
-    alpha_array::MVector{P, Float64} = zeros(MVector{P, Float64})
-    v_a_array::MVector{P, Float64} = zeros(MVector{P, Float64})
+    gamma_distribution::MVector{P, Float64} = zeros(P)
+    alpha_uncorrected::MVector{P, Float64} = zeros(P)
+    alpha_corrected::MVector{P, Float64} = zeros(P)
+    stall_angle_list::MVector{P, Float64} = zeros(P)
+    alpha_array::MVector{P, Float64} = zeros(P)
+    v_a_array::MVector{P, Float64} = zeros(P)
     work_vectors::NTuple{10,MVec3} = ntuple(_ -> zeros(MVec3), 10)
     AIC::Array{Float64, 3} = zeros(3, P, P)
     projected_area::Float64 = one(Float64)
-    y::MVector{P, Float64} = zeros(MVector{P, Float64})
+    y::MVector{P, Float64} = zeros(P)
     cache::Vector{PreallocationTools.LazyBufferCache{typeof(identity), typeof(identity)}} = [LazyBufferCache() for _ in 1:5]
 end
 
@@ -667,3 +667,44 @@ function set_va!(body_aero::BodyAerodynamics, va_distribution::Vector{VelVector}
     return nothing
 end
 
+"""
+    set_va!(body_aero::BodyAerodynamics, settings::VSMSettings)
+
+Set velocity array from VSM settings configuration.
+
+This convenience method extracts flight conditions from VSMSettings and 
+constructs the velocity vector in the body reference frame based on:
+- Wind speed from settings.condition.wind_speed
+- Angle of attack from settings.condition.alpha (converted from degrees)
+- Sideslip angle from settings.condition.beta (converted from degrees)
+
+The velocity vector is constructed as:
+- X_b (forward): wind_speed * cos(α) * cos(β)  
+- Y_b (right): wind_speed * sin(β)
+- Z_b (down): wind_speed * sin(α) * cos(β)
+
+# Arguments
+- `body_aero::BodyAerodynamics`: The aerodynamic body to modify
+- `settings::VSMSettings`: Settings object containing flight conditions
+
+# Example
+```julia
+settings = VSMSettings("path/to/settings.yaml")
+body_aero = BodyAerodynamics([wing])
+set_va!(body_aero, settings)
+```
+"""
+function set_va!(body_aero::BodyAerodynamics, settings::VSMSettings)
+    α = deg2rad(settings.condition.alpha)
+    β = deg2rad(settings.condition.beta)
+    wind_speed = settings.condition.wind_speed
+    
+    va = wind_speed * [
+        cos(α)*cos(β),  # X_b (forward)
+        sin(β),         # Y_b (right)
+        sin(α)*cos(β)   # Z_b (down)
+    ]
+    
+    set_va!(body_aero, va)
+end
+
diff --git a/src/plotting.jl b/src/plotting.jl
index 504e8ecd..3c602edb 100644
--- a/src/plotting.jl
+++ b/src/plotting.jl
@@ -349,9 +349,9 @@ function VortexStepMethod.plot_distribution(y_coordinates_list, results_list, la
     for (y_coordinates_i, result_i, label_i) in zip(y_coordinates_list, results_list, label_list)
         value = "$(round(result_i["cl"], digits=2))"
         if label_i == "LLT"
-            label = label_i * L" $~C_L$: " * value
+            label = label_i * L" $~C_\mathrm{L}$: " * value
         else
-            label = label_i * L" $C_L$: " * value
+            label = label_i * L" $C_\mathrm{L}$: " * value
         end
         axs[1, 1].plot(
             y_coordinates_i,
@@ -359,18 +359,18 @@ function VortexStepMethod.plot_distribution(y_coordinates_list, results_list, la
             label=label
         )
     end
-    axs[1, 1].set_title(L"$C_L$ Distribution", size=16)
+    axs[1, 1].set_title(L"$C_\mathrm{L}$ Distribution", size=16)
     axs[1, 1].set_xlabel(L"Spanwise Position $y/b$")
-    axs[1, 1].set_ylabel(L"Lift Coefficient $C_L$")
+    axs[1, 1].set_ylabel(L"Lift Coefficient $C_\mathrm{L}$")
     axs[1, 1].legend()
 
     # CD plot
     for (y_coordinates_i, result_i, label_i) in zip(y_coordinates_list, results_list, label_list)
         value = "$(round(result_i["cl"], digits=2))"
         if label_i == "LLT"
-            label = label_i * L" $~C_D$: " * value
+            label = label_i * L" $~C_\mathrm{D}$: " * value
         else
-            label = label_i * L" $C_D$: " * value
+            label = label_i * L" $C_\mathrm{D}$: " * value
         end
         axs[1, 2].plot(
             y_coordinates_i,
@@ -378,9 +378,9 @@ function VortexStepMethod.plot_distribution(y_coordinates_list, results_list, la
             label=label
         )
     end
-    axs[1, 2].set_title(L"$C_D$ Distribution", size=16)
+    axs[1, 2].set_title(L"$C_\mathrm{D}$ Distribution", size=16)
     axs[1, 2].set_xlabel(L"Spanwise Position $y/b$")
-    axs[1, 2].set_ylabel(L"Drag Coefficient $C_D$")
+    axs[1, 2].set_ylabel(L"Drag Coefficient $C_\mathrm{D}$")
     axs[1, 2].legend()
 
     # Gamma Distribution
@@ -645,15 +645,25 @@ function VortexStepMethod.plot_polars(
         # Update label with Reynolds number
         label_list[i] = "$(label_list[i]) Re = $(round(Int64, rey*1e-5))e5"
     end
-
     # Load literature data if provided
     if !isempty(literature_path_list)
         for path in literature_path_list
-            # Read all data first
             data = readdlm(path, ',')
-            # Skip the header row by taking data from row 2 onwards
-            data = data[2:end, :]
-            push!(polar_data_list, [data[:, 3], data[:, 1], data[:, 2], zeros(length(data[:, 1]))])
+            header = lowercase.(string.(data[1, :]))
+            # Find column indices for alpha, CL, CD, CS (case-insensitive, allow common variants)
+            alpha_idx = findfirst(x -> occursin("alpha", x), header)
+            cl_idx    = findfirst(x -> occursin("cl", x), header)
+            cd_idx    = findfirst(x -> occursin("cd", x), header)
+            cs_idx    = findfirst(x -> occursin("cs", x), header)
+            # Fallback: if CS not found, fill with zeros
+            cs_col = cs_idx === nothing ? zeros(size(data, 1)-1) : data[2:end, cs_idx]
+            # Push as [alpha, CL, CD, CS]
+            push!(polar_data_list, [
+                data[2:end, alpha_idx],
+                data[2:end, cl_idx],
+                data[2:end, cd_idx],
+                cs_col
+            ])
         end
     end
 
@@ -695,10 +705,10 @@ function VortexStepMethod.plot_polars(
         if maximum(polar_data[2]) > 10
             axs[1, 1].set_ylim([-0.5, 2])
         end
-        title = raw"$C_L" * raw"$" * " vs $angle_type [°]"
+        title = raw"$C_\mathrm{L}" * raw"$" * " vs $angle_type [°]"
         axs[1, 1].set_title(title)
         axs[1, 1].set_xlabel("$angle_type [°]")
-        axs[1, 1].set_ylabel(L"$C_L$")
+        axs[1, 1].set_ylabel(L"$C_\mathrm{L}$")
         axs[1, 1].legend()
     end
 
@@ -735,10 +745,10 @@ function VortexStepMethod.plot_polars(
         if maximum(polar_data[2]) > 10
             axs[1, 2].set_ylim([-0.5, 2])
         end
-        title = raw"$C_D" * raw"$" * " vs $angle_type [°]"
+        title = raw"$C_\mathrm{D}" * raw"$" * " vs $angle_type [°]"
         axs[1, 2].set_title(title)
         axs[1, 2].set_xlabel("$angle_type [°]")
-        axs[1, 2].set_ylabel(L"$C_D$")
+        axs[1, 2].set_ylabel(L"$C_\mathrm{D}$")
         axs[1, 2].legend()
     end
 
@@ -776,10 +786,10 @@ function VortexStepMethod.plot_polars(
         if maximum(polar_data[2]) > 10
             axs[2, 1].set_ylim([-0.5, 2])
         end
-        title = raw"$C_S" * raw"$" * " vs $angle_type [°]"
+        title = raw"$C_\mathrm{S}" * raw"$" * " vs $angle_type [°]"
         axs[2, 1].set_title(title)
         axs[2, 1].set_xlabel("$angle_type [°]")
-        axs[2, 1].set_ylabel(L"$C_S$")
+        axs[2, 1].set_ylabel(L"$C_\mathrm{S}$")
         axs[2, 1].legend()
     end
 
@@ -817,10 +827,10 @@ function VortexStepMethod.plot_polars(
             axs[2, 2].set_ylim([-0.5, 2])
             axs[2, 2].set_xlim([-0.5, 2])
         end
-        title = raw"$C_L" * raw"$" * " vs " * raw"$C_D" * raw"$"
+        title = raw"$C_\mathrm{L}" * raw"$" * " vs " * raw"$C_\mathrm{D}" * raw"$"
         axs[2, 2].set_title(title)
-        axs[2, 2].set_xlabel(L"$C_D$")
-        axs[2, 2].set_ylabel(L"$C_L$")
+        axs[2, 2].set_xlabel(L"$C_\mathrm{D}$")
+        axs[2, 2].set_ylabel(L"$C_\mathrm{L}$")
         axs[2, 2].legend()
     end
 
diff --git a/src/polars.jl b/src/polars.jl
index 902a4877..05957bc6 100644
--- a/src/polars.jl
+++ b/src/polars.jl
@@ -363,4 +363,3 @@ function read_aero_matrix(filepath::String)
     
     return matrix, alpha_values, delta_values
 end
-
diff --git a/src/precompile.jl b/src/precompile.jl
index c6f13e39..cd9a44ab 100644
--- a/src/precompile.jl
+++ b/src/precompile.jl
@@ -1,21 +1,16 @@
 @setup_workload begin
     # Putting some things in `@setup_workload` instead of `@compile_workload` can reduce the size of the
     # precompile file and potentially make loading faster.
-    # list = [OtherType("hello"), OtherType("world!")]
-    path = dirname(pathof(@__MODULE__))
-
+    
     @compile_workload begin
+        # Minimal precompilation to avoid segfault
         # all calls in this block will be precompiled, regardless of whether
         # they belong to your package or not (on Julia 1.8 and higher)
-        vss = vs(joinpath(path, "../data/vsm_settings_dual.yaml"))
+        
         # Step 1: Define wing parameters
-        n_panels = 20          # Number of panels
-        span = 20.0            # Wing span [m]
+        n_panels = 2           # Reduced number of panels for faster precompilation
+        span = 10.0            # Wing span [m]
         chord = 1.0            # Chord length [m]
-        v_a = 20.0             # Magnitude of inflow velocity [m/s]
-        density = 1.225        # Air density [kg/m³]
-        alpha_deg = 30.0       # Angle of attack [degrees]
-        alpha = deg2rad(alpha_deg)
 
         # Step 2: Create wing geometry with linear panel distribution
         wing = Wing(n_panels, spanwise_distribution=LINEAR)
@@ -30,11 +25,8 @@
             [chord, -span/2, 0.0], # Right tip TE
             INVISCID)
 
-        # Step 3: Initialize aerodynamics
-        body_aero::BodyAerodynamics = BodyAerodynamics([wing])
-
-        gamma_initial = zeros(length(body_aero.panels))
-        calculate_circulation_distribution_elliptical_wing(gamma_initial, body_aero)
+        # Step 3: Initialize aerodynamics (simplified)
+        body_aero = BodyAerodynamics([wing])
 
         nothing
     end
diff --git a/src/settings.jl b/src/settings.jl
index 65594076..fe538ed9 100644
--- a/src/settings.jl
+++ b/src/settings.jl
@@ -1,5 +1,13 @@
+@with_kw mutable struct ConditionSettings
+    wind_speed::Float64 = 10.0      # wind speed [m/s]
+    alpha::Float64 = 5.0            # angle of attack [°]
+    beta::Float64 = 0.0             # sideslip angle [°]
+    yaw_rate::Float64 = 0.0         # yaw rate [°/s]
+end
+
 @with_kw mutable struct WingSettings
     name::String = "main_wing"
+    geometry_file::String = ""          # path to wing geometry YAML file
     n_panels::Int64 = 40
     n_groups::Int64 = 40 
     spanwise_panel_distribution::PanelDistribution = LINEAR
@@ -11,6 +19,7 @@ end
     n_panels::Int64 = 40
     n_groups::Int64 = 40 
     aerodynamic_model_type::Model = VSM
+    solver_type::String = "LOOP"    # type of solver
     density::Float64 = 1.225                # air density  [kg/m³] 
     max_iterations::Int64 = 1500
     rtol::Float64 = 1e-5                    # relative error   [-]
@@ -26,54 +35,79 @@ end
 end
 
 @Base.kwdef mutable struct VSMSettings
+    condition::ConditionSettings = ConditionSettings()
     wings::Vector{WingSettings} = []
     solver_settings::SolverSettings = SolverSettings()
 end
 
-function vs(filename)
-    res = VSMSettings()
+function VSMSettings(filename)
+    # Uwe's suggested 3-line approach using StructMapping.jl (adapted)
     data = YAML.load_file(joinpath("data", filename))
+    
+    # Use StructMapping for basic structure conversion
+    # But handle special fields manually due to enum conversion needs
+    vsm_settings = VSMSettings()
+    
+    # Convert condition settings using StructMapping (if present)
+    if haskey(data, "condition")
+        vsm_settings.condition = convertdict(ConditionSettings, data["condition"])
+    end
+    
+    # Convert wing settings manually due to enum conversions
     n_panels = 0
     n_groups = 0
-    # add and update wing settings
-    for (i, wing) in pairs(data["wings"])
-        push!(res.wings, WingSettings())
-        res.wings[i].name = wing["name"]
-        res.wings[i].n_panels = wing["n_panels"]
-        n_panels += res.wings[i].n_panels
-        res.wings[i].n_groups = wing["n_groups"]
-        n_groups += res.wings[i].n_groups
-        res.wings[i].spanwise_panel_distribution = eval(Symbol(wing["spanwise_panel_distribution"]))
-        res.wings[i].spanwise_direction = MVec3(wing["spanwise_direction"])
-        res.wings[i].remove_nan = wing["remove_nan"]
+    
+    if haskey(data, "wings")
+        for wing_data in data["wings"]
+            wing = WingSettings()
+            wing.name = wing_data["name"]
+            if haskey(wing_data, "geometry_file")
+                wing.geometry_file = wing_data["geometry_file"]
+            end
+            wing.n_panels = wing_data["n_panels"]
+            wing.n_groups = wing_data["n_groups"]
+            wing.spanwise_panel_distribution = eval(Symbol(wing_data["spanwise_panel_distribution"]))
+            wing.spanwise_direction = MVec3(wing_data["spanwise_direction"])
+            wing.remove_nan = wing_data["remove_nan"]
+            
+            push!(vsm_settings.wings, wing)
+            n_panels += wing.n_panels
+            n_groups += wing.n_groups
+        end
+    end
+    
+    # Convert solver settings using StructMapping base, then override special fields
+    if haskey(data, "solver_settings")
+        solver_data = data["solver_settings"]
+        
+        # Create a copy of solver_data with string fields for enums removed
+        solver_data_clean = copy(solver_data)
+        delete!(solver_data_clean, "aerodynamic_model_type")
+        delete!(solver_data_clean, "type_initial_gamma_distribution")
+        
+        # Use StructMapping for the basic fields
+        vsm_settings.solver_settings = convertdict(SolverSettings, solver_data_clean)
+        
+        # Handle enum conversions manually
+        vsm_settings.solver_settings.aerodynamic_model_type = eval(Symbol(solver_data["aerodynamic_model_type"]))
+        vsm_settings.solver_settings.type_initial_gamma_distribution = eval(Symbol(solver_data["type_initial_gamma_distribution"]))
+        
+        # Override with calculated totals
+        vsm_settings.solver_settings.n_panels = n_panels
+        vsm_settings.solver_settings.n_groups = n_groups
     end
-    # update solver settings
-    solver = data["solver_settings"]
-    res.solver_settings.n_panels = n_panels
-    res.solver_settings.n_groups = n_groups
-    res.solver_settings.aerodynamic_model_type = eval(Symbol(solver["aerodynamic_model_type"]))
-    res.solver_settings.density = solver["density"]
-    res.solver_settings.max_iterations = solver["max_iterations"]
-    res.solver_settings.rtol = solver["rtol"]
-    res.solver_settings.tol_reference_error = solver["tol_reference_error"]
-    res.solver_settings.relaxation_factor = solver["relaxation_factor"]
-    res.solver_settings.artificial_damping = solver["artificial_damping"]
-    res.solver_settings.k2 = solver["k2"]
-    res.solver_settings.k4 = solver["k4"]
-    res.solver_settings.type_initial_gamma_distribution = eval(Symbol(solver["type_initial_gamma_distribution"]))
-    res.solver_settings.core_radius_fraction = solver["core_radius_fraction"]
-    res.solver_settings.mu = solver["mu"]
-    res.solver_settings.calc_only_f_and_gamma = solver["calc_only_f_and_gamma"]
-    res
+    
+    return vsm_settings
 end
 
-function Base.show(io::IO, vs::VSMSettings)
+function Base.show(io::IO, vsm_settings::VSMSettings)
     println(io, "VSMSettings:")
-    for (i, wing) in pairs(vs.wings)
+    print(io, replace(repr(vsm_settings.condition), "\n" => "\n    "))
+    for (i, wing) in pairs(vsm_settings.wings)
         if i==1
             print(io, "    ")
         end
         print(io, replace(repr(wing), "\n" => "\n    "))
     end
-    print(io, replace(repr(vs.solver_settings), "\n" => "\n    "))
-end
+    print(io, replace(repr(vsm_settings.solver_settings), "\n" => "\n    "))
+end
\ No newline at end of file
diff --git a/src/solver.jl b/src/solver.jl
index 36a8b632..f3ea1085 100644
--- a/src/solver.jl
+++ b/src/solver.jl
@@ -47,23 +47,23 @@ Struct for storing the solution of the [solve!](@ref) function. Must contain all
     moment::MVec3 = zeros(MVec3)       
     force_coeffs::MVec3 = zeros(MVec3)  
     moment_coeffs::MVec3 = zeros(MVec3)  
-    moment_dist::MVector{P, Float64} = zeros(MVector{P, Float64})
-    moment_coeff_dist::MVector{P, Float64} = zeros(MVector{P, Float64})
-    group_moment_dist::MVector{G, Float64} = zeros(MVector{G, Float64})
-    group_moment_coeff_dist::MVector{G, Float64} = zeros(MVector{G, Float64})
+    moment_dist::MVector{P, Float64} = zeros(P)
+    moment_coeff_dist::MVector{P, Float64} = zeros(P)
+    group_moment_dist::MVector{G, Float64} = zeros(G)
+    group_moment_coeff_dist::MVector{G, Float64} = zeros(G)
     solver_status::SolverStatus = FAILURE
 end
 
 # Output of the function gamma_loop!
 @with_kw mutable struct LoopResult{P}
     converged::Bool              = false
-    gamma_new::MVector{P, Float64}   = zeros(MVector{P, Float64})
-    alpha_array::MVector{P, Float64} = zeros(MVector{P, Float64}) # TODO: Is this different from BodyAerodynamics.alpha_array ?
-    v_a_array::MVector{P, Float64}   = zeros(MVector{P, Float64})
+    gamma_new::MVector{P, Float64}   = zeros(P)
+    alpha_array::MVector{P, Float64} = zeros(P) # TODO: Is this different from BodyAerodynamics.alpha_array ?
+    v_a_array::MVector{P, Float64}   = zeros(P)
 end
 
 @with_kw struct BaseResult{P}
-    va_norm_array::MVector{P, Float64} = zeros(MVector{P, Float64})
+    va_norm_array::MVector{P, Float64} = zeros(P)
     va_unit_array::Matrix{Float64} = zeros(P, 3)
 end
 
@@ -137,6 +137,17 @@ function Solver(body_aero; kwargs...)
     return Solver{P,G}(; kwargs...)
 end
 
+function Solver(body_aero, settings::VSMSettings)
+    Solver(body_aero;
+        aerodynamic_model_type=settings.solver_settings.aerodynamic_model_type,
+        density=settings.solver_settings.density,
+        max_iterations=settings.solver_settings.max_iterations,
+        rtol=settings.solver_settings.rtol,
+        relaxation_factor=settings.solver_settings.relaxation_factor,
+        core_radius_fraction=settings.solver_settings.core_radius_fraction,
+    )
+end
+
 """
     solve!(solver::Solver, body_aero::BodyAerodynamics, gamma_distribution=solver.sol.gamma_distribution; 
           log=false, reference_point=zeros(MVec3), moment_frac=0.1)
diff --git a/src/wing_geometry.jl b/src/wing_geometry.jl
index d7950894..506b91b4 100644
--- a/src/wing_geometry.jl
+++ b/src/wing_geometry.jl
@@ -1,4 +1,3 @@
-
 """
     @with_kw mutable struct Section
 
diff --git a/src/yaml_geometry.jl b/src/yaml_geometry.jl
new file mode 100644
index 00000000..1abf3118
--- /dev/null
+++ b/src/yaml_geometry.jl
@@ -0,0 +1,301 @@
+# Data structures for YAML wing geometry
+@with_kw struct WingAirfoilInfo
+    csv_file_path::String
+end
+
+@with_kw struct WingSectionData
+    airfoil_id::Int64
+    LE_x::Float64
+    LE_y::Float64
+    LE_z::Float64
+    TE_x::Float64
+    TE_y::Float64
+    TE_z::Float64
+end
+
+@with_kw struct WingAirfoilData
+    airfoil_id::Int64
+    type::String
+    info_dict::WingAirfoilInfo
+end
+
+"""
+    load_polar_data(csv_file_path::String) -> Tuple{Union{Nothing, Tuple{Vector{Float64}, Vector{Float64}, Vector{Float64}, Vector{Float64}}}, Symbol}
+
+Load aerodynamic polar data from a CSV file using only `readlines`.
+
+The CSV file must contain a header row with columns for `alpha`, `cl`, `cd`, and `cm` (case-insensitive, order arbitrary). Each subsequent row should contain numeric values for these columns.
+
+# Arguments
+- `csv_file_path::String`: Path to the CSV file containing polar data.
+
+# Returns
+- A tuple `(aero_data, model_type)` where:
+    - `aero_data`: A tuple of vectors `(alpha, cl, cd, cm)` if the file is valid, or `nothing` if invalid or missing.
+        - `alpha`: Angle of attack in degrees (converted to radians internally).
+        - `cl`: Lift coefficient.
+        - `cd`: Drag coefficient.
+        - `cm`: Moment coefficient.
+    - `model_type`: `POLAR_VECTORS` if data is loaded, or `INVISCID` if not.
+
+# Behavior
+- If the file is missing, empty, or invalid, a warning is issued and `(nothing, INVISCID)` is returned.
+
+# Example
+```julia
+# Create a YAML-based wing from configuration file
+wing = Wing(
+    "path/to/wing_config.yaml";
+    n_panels=40,
+    n_groups=4
+)
+```
+"""
+function load_polar_data(csv_file_path::String)
+    # Return early for empty path
+    if isempty(csv_file_path)
+        @warn "Empty CSV file path provided"
+        return (nothing, INVISCID)
+    end
+
+    # Check if file exists
+    if !isfile(csv_file_path)
+        @warn "CSV file not found: $csv_file_path"
+        return (nothing, INVISCID)
+    end
+
+    try
+        # Read all lines from the file
+        lines = readlines(csv_file_path)
+        
+        # Check if file is empty
+        if isempty(lines)
+            @warn "CSV file is empty: $csv_file_path"
+            return (nothing, INVISCID)
+        end
+
+        # Parse header - make case insensitive
+        header_line = strip(lines[1])
+        if isempty(header_line)
+            @warn "CSV file has empty header: $csv_file_path"
+            return (nothing, INVISCID)
+        end
+
+        # Split header and normalize to lowercase
+        header_parts = map(strip ∘ lowercase, split(header_line, ','))
+        
+        # Find column indices for required columns
+        required_cols = ["alpha", "cl", "cd", "cm"]
+        col_indices = Dict{String, Int}()
+        
+        for (i, col_name) in enumerate(header_parts)
+            if col_name in required_cols
+                col_indices[col_name] = i
+            end
+        end
+        
+        # Check if all required columns are present
+        missing_cols = setdiff(required_cols, keys(col_indices))
+        if !isempty(missing_cols)
+            @warn "CSV file missing required columns: $(join(missing_cols, ", ")) in $csv_file_path"
+            return (nothing, INVISCID)
+        end
+
+        # Parse data rows
+        data_vectors = Dict{String, Vector{Float64}}()
+        for col in required_cols
+            data_vectors[col] = Float64[]
+        end
+
+        for line_num in 2:length(lines)
+            line = strip(lines[line_num])
+            isempty(line) && continue  # Skip empty lines
+            
+            parts = split(line, ',')
+            if length(parts) != length(header_parts)
+                @warn "Line $line_num has incorrect number of columns in $csv_file_path"
+                return (nothing, INVISCID)  # Strict: any malformed data rejects the file
+            end
+
+            try
+                for col in required_cols
+                    value_str = strip(parts[col_indices[col]])
+                    value = parse(Float64, value_str)
+                    push!(data_vectors[col], value)
+                end
+            catch e
+                @warn "Failed to parse line $line_num in $csv_file_path: $e"
+                return (nothing, INVISCID)  # Strict: any parsing error rejects the file
+            end
+        end
+
+        # Check if we got any valid data
+        if isempty(data_vectors["alpha"])
+            @warn "No valid data rows found in $csv_file_path"
+            return (nothing, INVISCID)
+        end
+
+        # Convert alpha from degrees to radians and create tuple
+        alpha_rad = deg2rad.(data_vectors["alpha"])
+        aero_data = (alpha_rad, data_vectors["cl"], data_vectors["cd"], data_vectors["cm"])
+        
+        return (aero_data, POLAR_VECTORS)
+
+    catch e
+        @warn "Error reading CSV file $csv_file_path: $e"
+        return (nothing, INVISCID)
+    end
+end
+
+"""
+    Wing(geometry_file::String; n_panels=20, n_groups=1, spanwise_distribution=LINEAR,
+         spanwise_direction=[0.0, 1.0, 0.0], remove_nan=true, prn=false)
+
+Constructs a `Wing` object from a YAML geometry file.
+
+# Arguments
+- `geometry_file::String`: Path to a YAML file describing the wing geometry and airfoils.
+
+# Keyword Arguments
+- `n_panels::Int`: Number of spanwise panels (default: 20).
+- `n_groups::Int`: Number of grouped sections across the span (default: 1). Must divide `n_panels`.
+- `spanwise_distribution`: Spanwise panel distribution type (default: `LINEAR`).
+- `spanwise_direction::Vector{Float64}`: Direction of the spanwise axis (default: `[0.0, 1.0, 0.0]`). Must be the global Y axis.
+- `remove_nan::Bool`: Remove NaN values from the geometry (default: `true`).
+- `prn::Bool`: Print informational messages during construction (default: `false`).
+
+# Returns
+- `Wing`: A fully constructed and initialized `Wing` object.
+
+# Description
+This function reads a YAML configuration file to define the geometry and airfoil data for a multi-section wing.
+Each section and corresponding airfoil is parsed from the YAML file, polar data is loaded, and each section is added
+to the wing. The geometry logic currently assumes the spanwise direction is `[0.0, 1.0, 0.0]` (aligned with the global Y axis).
+
+# Errors
+- Throws an `ArgumentError` if `n_panels` is not divisible by `n_groups`.
+- Throws an `ArgumentError` if `spanwise_direction` is not `[0.0, 1.0, 0.0]`.
+
+# Example
+```julia
+wing = Wing("wing_geometry.yaml"; n_panels=30, n_groups=2, prn=true)
+```
+"""
+function Wing(
+    geometry_file::String;
+    n_panels=20,
+    n_groups=1,
+    spanwise_distribution=LINEAR,
+    spanwise_direction=[0.0, 1.0, 0.0],
+    remove_nan=true,
+    prn=false
+)
+    !(n_panels % n_groups == 0) && throw(ArgumentError("Number of panels should be divisible by number of groups"))
+    !isapprox(spanwise_direction, [0.0, 1.0, 0.0]) && throw(ArgumentError("Spanwise direction has to be [0.0, 1.0, 0.0], not $spanwise_direction"))
+    
+    prn && @info "Reading YAML wing configuration from $geometry_file"
+    
+    # Load YAML file following Uwe's suggestion
+    data = YAML.load_file(geometry_file)
+
+    # Convert YAML data to our struct format
+    # Convert wing sections
+    wing_sections_data = data["wing_sections"]
+    sections = WingSectionData[]
+    for row in wing_sections_data["data"]
+        section_dict = Dict(zip(wing_sections_data["headers"], row))
+        push!(sections, WingSectionData(
+            airfoil_id = section_dict["airfoil_id"],
+            LE_x = section_dict["LE_x"],
+            LE_y = section_dict["LE_y"], 
+            LE_z = section_dict["LE_z"],
+            TE_x = section_dict["TE_x"],
+            TE_y = section_dict["TE_y"],
+            TE_z = section_dict["TE_z"]
+        ))
+    end
+    
+    # Convert wing airfoils
+    wing_airfoils_data = data["wing_airfoils"]
+    airfoils = WingAirfoilData[]
+    for row in wing_airfoils_data["data"]
+        airfoil_dict = Dict(zip(wing_airfoils_data["headers"], row))
+        push!(airfoils, WingAirfoilData(
+            airfoil_id = airfoil_dict["airfoil_id"],
+            type = airfoil_dict["type"],
+            info_dict = WingAirfoilInfo(csv_file_path = get(airfoil_dict["info_dict"], "csv_file_path", ""))
+        ))
+    end
+    
+    # Create CSV file mapping from airfoils
+    airfoil_csv_map = Dict{Int64, String}()
+    for airfoil in airfoils
+        if !isempty(airfoil.info_dict.csv_file_path)
+            airfoil_csv_map[airfoil.airfoil_id] = airfoil.info_dict.csv_file_path
+        end
+    end
+    
+    # Create Wing using the standard constructor
+    wing = Wing(n_panels; 
+        n_groups=n_groups, 
+        spanwise_distribution=spanwise_distribution,
+        spanwise_direction=MVec3(spanwise_direction), 
+        remove_nan=remove_nan
+    )
+    
+    # Parse sections and populate wing
+    for section in sections
+        # Get coordinates directly from struct fields
+        le_coord = [section.LE_x, section.LE_y, section.LE_z]
+        te_coord = [section.TE_x, section.TE_y, section.TE_z]
+        
+        # Load polar data and create section
+        csv_file_path = get(airfoil_csv_map, section.airfoil_id, "")
+        if !isempty(csv_file_path) && !isabspath(csv_file_path)
+            # NOTE: The spanwise direction is currently restricted to [0.0, 1.0, 0.0] (the global Y axis).
+            # This is required because downstream geometry and panel generation code assumes the spanwise axis is aligned with Y.
+            # If you need to support arbitrary spanwise directions, refactor the geometry logic accordingly.
+            csv_file_path = joinpath(dirname(geometry_file), csv_file_path)
+        end
+        aero_data, aero_model = load_polar_data(csv_file_path)
+        
+        prn && println("Section airfoil_id $(section.airfoil_id): Using $aero_model model")
+        
+        add_section!(wing, le_coord, te_coord, aero_model, aero_data)
+    end
+    
+    # Initialize the wing after adding all sections
+    reinit!(wing)
+    
+    return wing
+end
+
+"""
+    Wing(settings::VSMSettings)
+
+Create a wing model from VSM settings configuration.
+
+This constructor is a convenience wrapper that extracts wing configuration 
+from VSMSettings and creates a Wing using the YAML geometry file path and 
+parameters specified in the settings.
+
+# Arguments
+- `settings`: VSMSettings object containing wing configuration
+
+# Returns
+A fully initialized `Wing` instance ready for aerodynamic simulation.
+
+# Example
+```julia
+# Load settings and create wing in one step
+settings = VSMSettings("path/to/vsm_settings.yaml")
+wing = Wing(settings)
+```
+"""
+function Wing(settings::VSMSettings)
+    Wing(settings.wings[1].geometry_file; 
+        n_panels=settings.wings[1].n_panels, 
+        n_groups=settings.wings[1].n_groups,
+        spanwise_distribution=settings.wings[1].spanwise_panel_distribution
+    )
+end
diff --git a/test/aqua.jl b/test/Aqua.jl
similarity index 96%
rename from test/aqua.jl
rename to test/Aqua.jl
index 89ce2df0..34474582 100644
--- a/test/aqua.jl
+++ b/test/Aqua.jl
@@ -5,4 +5,4 @@ using Aqua
       stale_deps=(ignore=[:Xfoil, :Timers, :PyCall],),
       deps_compat=(ignore=[:PyCall],)
     )
-  end
+end
diff --git a/test/README.md b/test/README.md
new file mode 100644
index 00000000..188c01a5
--- /dev/null
+++ b/test/README.md
@@ -0,0 +1,72 @@
+# Test Data Organization
+
+This directory contains organized test data for the VortexStepMethod.jl test suite.
+
+## Running Tests
+
+You can run tests in different ways:
+```bash
+# Run all tests
+julia --project=. test/runtests.jl
+```
+```bash
+# Run specific test files
+julia --project=. test/yaml_geometry/test_yaml_geometry.jl
+julia --project=. test/body_aerodynamics/test_body_aerodynamics.jl
+julia --project=. test/solver/test_solver.jl
+# etc.
+```
+## Adding New Test Data
+
+When adding test data for a new source module:
+
+1. Create test files in the appropriate module directory under `test/`
+2. Add any required data files (YAML, CSV) in the same directory
+3. Use `test_data_path()` helper function to access files with proper paths
+4. Follow the existing naming conventions
+
+
+## Structure
+
+The test data is organized by source module being tested, following the structure of the `src/` directory:
+
+```
+test/
+├── body_aerodynamics/          # Tests for src/body_aerodynamics.jl
+│   ├── test_body_aerodynamics.jl
+│   ├── test_results.jl
+│   └── test_wing.yaml         # Wing geometry for body aero tests
+├── yaml_geometry/              # Tests for src/yaml_geometry.jl
+│   ├── test_yaml_geometry.jl
+│   ├── simple_wing.yaml       # Basic 2-section wing
+│   ├── complex_wing.yaml      # Multi-section wing
+│   ├── standard_airfoil.csv   # Standard polar data
+│   └── alternate_airfoil.csv  # Alternative airfoil data
+├── solver/                     # Tests for src/solver.jl
+│   ├── test_solver.jl
+│   ├── solver_settings.yaml   # Settings for solver tests
+│   ├── solver_test_polar.csv  # Polar data for solver tests
+│   └── solver_test_wing.yaml  # Wing for solver tests
+├── settings/                   # Tests for src/settings.jl
+│   └── test_settings.jl
+├── filament/                   # Tests for src/filament.jl
+│   ├── test_bound_filament.jl
+│   └── test_semi_infinite_filament.jl
+├── panel/                      # Tests for src/panel.jl
+│   └── test_panel.jl
+├── plotting/                   # Tests for src/plotting.jl
+│   └── test_plotting.jl
+├── polars/                     # Tests for src/polars.jl
+│   └── test_polars.jl
+├── ram_geometry/               # Tests for src/ram_geometry.jl
+│   └── test_kite_geometry.jl
+├── wake/                       # Tests for src/wake.jl
+│   └── test_wake.jl
+├── wing_geometry/              # Tests for src/wing_geometry.jl
+│   └── test_wing_geometry.jl
+├── VortexStepMethod/           # Tests for main module
+│   └── test_VortexStepMethod.jl
+├── test_data_utils.jl          # Shared utilities for test data access
+├── runtests.jl                 # Main test runner
+└── README.md                   # This file
+```
diff --git a/test/TestSupport.jl b/test/TestSupport.jl
new file mode 100644
index 00000000..4b428502
--- /dev/null
+++ b/test/TestSupport.jl
@@ -0,0 +1,5 @@
+module TestSupport
+export suppress_warnings, test_data_path, create_temp_wing_settings,
+       get_standard_wing_file, get_complete_settings_file
+include("test_data_utils.jl")
+end
\ No newline at end of file
diff --git a/test/VortexStepMethod/test_VortexStepMethod.jl b/test/VortexStepMethod/test_VortexStepMethod.jl
new file mode 100644
index 00000000..85175440
--- /dev/null
+++ b/test/VortexStepMethod/test_VortexStepMethod.jl
@@ -0,0 +1 @@
+##TODO: populate
\ No newline at end of file
diff --git a/test/body_aerodynamics/complete_settings.yaml b/test/body_aerodynamics/complete_settings.yaml
new file mode 100644
index 00000000..a40ff608
--- /dev/null
+++ b/test/body_aerodynamics/complete_settings.yaml
@@ -0,0 +1,18 @@
+wings:
+  - name: "body_aero_test_wing"
+    geometry_file: "test/body_aerodynamics/test_wing.yaml"
+    n_panels: 4
+    n_groups: 2
+    spanwise_panel_distribution: COSINE
+    spanwise_direction: [0.0, 1.0, 0.0]
+    remove_nan: true
+
+solver_settings:
+  aerodynamic_model_type: VSM
+  density: 1.225
+  type_initial_gamma_distribution: ZEROS
+
+condition:
+  alpha: 10.0
+  beta: 5.0
+  wind_speed: 15.0
diff --git a/test/body_aerodynamics/simple_polar.csv b/test/body_aerodynamics/simple_polar.csv
new file mode 100644
index 00000000..7e043d9c
--- /dev/null
+++ b/test/body_aerodynamics/simple_polar.csv
@@ -0,0 +1,4 @@
+alpha,cl,cd,cm
+-10.0,0.1,0.02,-0.01
+0.0,1.0,0.01,0.0
+10.0,1.8,0.025,0.01
diff --git a/test/body_aerodynamics/test_body_aerodynamics.jl b/test/body_aerodynamics/test_body_aerodynamics.jl
new file mode 100644
index 00000000..c022102f
--- /dev/null
+++ b/test/body_aerodynamics/test_body_aerodynamics.jl
@@ -0,0 +1,436 @@
+using VortexStepMethod
+using VortexStepMethod: calculate_cl, calculate_cd_cm, calculate_projected_area, calculate_AIC_matrices!
+using LinearAlgebra
+using Test
+using Logging
+
+include("../utils.jl")
+
+@testset "Induction Matrix Creation" begin
+    # Setup
+    n_panels = 3
+    N = n_panels + 1  # number of SECTIONS
+    max_chord = 1.0
+    span = 2.36
+    AR = span^2 / (π * span * max_chord / 4)
+    dist = "cos"
+    coord = generate_coordinates_el_wing(max_chord, span, N, dist)
+
+    Atot = max_chord / 2 * span / 2 * π
+    @debug "N: $N"
+    @debug "size(coord): $(size(coord))"
+
+    v_a = 20.0
+    aoa = 5.7106 * π / 180
+    v_a = [cos(aoa), 0.0, sin(aoa)] .* v_a
+
+    # Create wing geometry
+    core_radius_fraction = 1e-20
+    coord_left_to_right = flip_created_coord_in_pairs(deepcopy(coord))
+    wing = Wing(n_panels; spanwise_distribution=UNCHANGED)
+    for idx in 1:2:size(coord_left_to_right, 1)
+        add_section!(
+            wing,
+            coord_left_to_right[idx,:],
+            coord_left_to_right[idx+1,:],
+            INVISCID
+        )
+    end
+    
+    body_aero = BodyAerodynamics([wing])
+    set_va!(body_aero, v_a)
+
+    # Calculate reference matrices using thesis functions
+    controlpoints, rings, bladepanels, ringvec, coord_L = 
+        create_geometry_general(coord, v_a, N, "5fil", LLT)
+    
+    # Test LLT matrices
+    @testset "LLT Matrices" begin
+        # Calculate reference matrices
+        MatrixU, MatrixV, MatrixW = thesis_induction_matrix_creation(
+            deepcopy(ringvec),
+            deepcopy(controlpoints),
+            deepcopy(rings),
+            deepcopy(v_a),
+            zeros(N-1),
+            nothing,  # data_airf not needed
+            nothing,  # conv_crit not needed
+            LLT
+        )
+
+        # Calculate new matrices
+        va_norm_array = fill(norm(v_a), length(coord))
+        va_unit_array = repeat(reshape(v_a ./ norm(v_a), 1, 3), length(coord))
+        calculate_AIC_matrices!(
+            body_aero,
+            LLT,
+            core_radius_fraction,
+            va_norm_array,
+            va_unit_array
+        )
+        AIC_x, AIC_y, AIC_z = @views body_aero.AIC[1, :, :], body_aero.AIC[2, :, :], body_aero.AIC[3, :, :]
+
+        # Compare matrices
+        @test isapprox(MatrixU, AIC_x, atol=1e-5)
+        @test isapprox(MatrixV, -AIC_y, atol=1e-5)
+        @test isapprox(MatrixW, AIC_z, atol=1e-5)
+    end
+
+    # Test VSM matrices
+    @testset "VSM Matrices" begin
+        # Calculate reference matrices for VSM
+        controlpoints, rings, bladepanels, ringvec, coord_L = 
+            create_geometry_general(coord, v_a, N, "5fil", VSM)
+        
+        MatrixU, MatrixV, MatrixW = thesis_induction_matrix_creation(
+            deepcopy(ringvec),
+            deepcopy(controlpoints),
+            deepcopy(rings),
+            deepcopy(v_a),
+            zeros(N-1),
+            nothing,
+            nothing,
+            VSM
+        )
+
+        # Calculate new matrices
+        va_norm_array = fill(norm(v_a), length(coord))
+        va_unit_array = repeat(reshape(v_a ./ norm(v_a), 1, 3), length(coord))
+        calculate_AIC_matrices!(
+            body_aero,
+            VSM,
+            core_radius_fraction,
+            va_norm_array,
+            va_unit_array
+        )
+        AIC_x, AIC_y, AIC_z = body_aero.AIC[1, :, :], body_aero.AIC[2, :, :], body_aero.AIC[3, :, :]
+
+        # Compare matrices with higher precision for VSM
+        @test isapprox(MatrixU, AIC_x, atol=1e-8)
+        @test isapprox(MatrixV, -AIC_y, atol=1e-8)
+        @test isapprox(MatrixW, AIC_z, atol=1e-8)
+    end
+end
+
+
+@testset "Wing Geometry Creation" begin
+    @testset "Origin Translation" begin
+        # Create minimal wing with three sections (2 panels)
+        wing = Wing(2)
+        add_section!(wing, [0.0, 0.0, 0.0], [1.0, 0.0, 0.0], INVISCID)
+        add_section!(wing, [0.0, 1.0, 0.0], [1.0, 1.0, 0.0], INVISCID)
+        add_section!(wing, [0.0, 2.0, 0.0], [1.0, 2.0, 0.0], INVISCID)
+    
+        # Test non-zero origin translation
+        origin = MVec3(1.0, 2.0, 3.0)
+        body_aero = BodyAerodynamics([wing]; kite_body_origin=origin)
+        
+        # Check if sections are correctly translated
+        @test wing.sections[3].LE_point ≈ [-1.0, -2.0, -3.0]
+        @test wing.sections[3].TE_point ≈ [0.0, -2.0, -3.0]
+        @test wing.sections[2].LE_point ≈ [-1.0, -1.0, -3.0]
+        @test wing.sections[2].TE_point ≈ [0.0, -1.0, -3.0]
+        @test wing.sections[1].LE_point ≈ [-1.0, 0.0, -3.0]
+        @test wing.sections[1].TE_point ≈ [0.0, 0.0, -3.0]
+    end
+
+    function create_geometry(; model=VSM, wing_type=:rectangular, plotting=false, N=40)
+        max_chord = 1.0
+        span = 17.0
+        AR = span^2 / (π * span * max_chord / 4)
+        @debug "AR: $AR"
+        v_a = 20.0
+        aoa = 5.7106 * π / 180
+        v_a = [cos(aoa), 0.0, sin(aoa)] .* v_a
+    
+        coord = if wing_type === :rectangular
+            theta = range(-0.5, 0.5, length=N)
+            beta = range(-2, 2, length=N)
+            generate_coordinates_rect_wing(
+                fill(max_chord, N),
+                span,
+                theta,
+                beta,
+                N,
+                "lin"
+            )
+        elseif wing_type === :curved
+            generate_coordinates_curved_wing(
+                max_chord, span, π/4, 5, N, "cos"
+            )
+        elseif wing_type === :elliptical
+            generate_coordinates_el_wing(max_chord, span, N, "cos")
+        else
+            error("Invalid wing type")
+        end
+    
+        coord_left_to_right = flip_created_coord_in_pairs(deepcopy(coord))
+        wing = Wing(N-1; spanwise_distribution=UNCHANGED)
+        for i in 1:2:size(coord_left_to_right, 1)
+            add_section!(
+                wing,
+                coord_left_to_right[i,:],
+                coord_left_to_right[i+1,:],
+                INVISCID
+            )
+        end
+        body_aero = BodyAerodynamics([wing])
+        set_va!(body_aero, v_a)
+        
+        return body_aero, coord, v_a, model
+    end
+
+    for model in [VSM, LLT]
+        @debug "model: $model"
+        for wing_type in [:rectangular, :curved, :elliptical]
+            @debug "wing_type: $wing_type"
+            body_aero, coord, v_a, model = create_geometry(
+                model=model, wing_type=wing_type
+            )
+            
+            # Generate geometry
+            expected_controlpoints, expected_rings, expected_bladepanels, 
+                expected_ringvec, expected_coord_L = create_geometry_general(
+                coord, v_a, div(size(coord,1), 2), "5fil", model
+            )
+
+            for i in 1:length(body_aero.panels)
+                @debug "i: $i"
+                # Handle control points
+                index_reversed = length(body_aero.panels) - i + 1
+                panel = body_aero.panels[index_reversed]
+                
+                evaluation_point = if model === VSM
+                    panel.control_point
+                else  # LLT
+                    panel.aero_center
+                end
+
+                @test isapprox(evaluation_point, expected_controlpoints[i]["coordinates"], atol=1e-4)
+                @test isapprox(panel.chord, expected_controlpoints[i]["chord"], atol=1e-4)
+                @test isapprox(panel.z_airf, expected_controlpoints[i]["normal"], atol=1e-4)
+                @test isapprox(panel.x_airf, expected_controlpoints[i]["tangential"], atol=1e-4)
+                @test isapprox(
+                    hcat(panel.z_airf, panel.x_airf, panel.y_airf),
+                    expected_controlpoints[i]["airf_coord"],
+                    atol=1e-4
+                )
+                
+                if model === VSM
+                    @test isapprox(
+                        panel.aero_center,
+                        expected_controlpoints[i]["coordinates_aoa"],
+                        atol=1e-4
+                    )
+                end
+
+                # Handle rings
+                expected_ring_i = expected_rings[i]
+                expected_ring_i_list = [
+                    expected_ring_i[1],
+                    expected_ring_i[2],
+                    expected_ring_i[3],
+                    expected_ring_i[4],
+                    expected_ring_i[5]
+                ]
+
+                filaments = panel.filaments
+                filament_list = [
+                    filaments[1],
+                    filaments[3],
+                    filaments[5],
+                    filaments[2],
+                    filaments[4]
+                ]
+
+                for (j, fil) in enumerate(filament_list)
+                    if j == 1  # bound filaments
+                        @test isapprox(fil.x1, expected_ring_i_list[j]["x1"], atol=1e-4)
+                        @test isapprox(fil.x2, expected_ring_i_list[j]["x2"], atol=1e-4)
+                    elseif j ∈ (2, 4)  # trailing filaments
+                        @test isapprox(fil.x1, expected_ring_i_list[j]["x1"], atol=1e-4)
+                        @test isapprox(fil.x2, expected_ring_i_list[j]["x2"], atol=1e-4)
+                    else  # semi-infinite filaments
+                        @test isapprox(fil.x1, expected_ring_i_list[j]["x1"], atol=1e-4)
+                    end
+                end
+
+                # Handle bladepanels
+                exp_bladepanels = expected_bladepanels[i]
+                @test isapprox(panel.LE_point_2, exp_bladepanels["p1"], atol=1e-4)
+                @test isapprox(panel.LE_point_1, exp_bladepanels["p2"], atol=1e-4)
+                @test isapprox(panel.TE_point_1, exp_bladepanels["p3"], atol=1e-4)
+                @test isapprox(panel.TE_point_2, exp_bladepanels["p4"], atol=1e-4)
+
+                # Handle ringvec
+                exp_ringvec = expected_ringvec[i]
+                r0 = panel.bound_point_1 - panel.bound_point_2
+                r3 = evaluation_point - (panel.bound_point_1 + panel.bound_point_2) / 2
+                @test isapprox(r0, exp_ringvec["r0"], atol=1e-4)
+                @test isapprox(r3, exp_ringvec["r3"], atol=1e-4)
+
+                # Handle coord_L
+                @test all(isapprox.(panel.aero_center, expected_coord_L[:, i]))
+            end
+        end
+    end
+end
+
+@testset "Calculate results against output results" begin
+    # Setup
+    density = 1.225
+    N = 40
+    max_chord = 1.0
+    span = 15.709  # AR = 20
+    v_a = 20.0
+    AR = span^2 / (π * span * max_chord / 4)
+    aoa = deg2rad(5)
+    v_a = [cos(aoa), 0.0, sin(aoa)] .* v_a
+    model = VSM
+
+    # Setup wing geometry
+    dist = "cos"
+    core_radius_fraction = 1e-20
+    coord = generate_coordinates_el_wing(max_chord, span, N, dist)
+    coord_left_to_right = flip_created_coord_in_pairs(deepcopy(coord))
+    wing = Wing(N-1; spanwise_distribution=UNCHANGED)
+    for idx in 1:2:length(coord_left_to_right[:, 1])
+        @debug "coord_left_to_right[$idx] = $(coord_left_to_right[idx,:])"
+        add_section!(
+            wing,
+            coord_left_to_right[idx,:],
+            coord_left_to_right[idx+1,:],
+            INVISCID
+        )
+    end
+    
+    body_aero = BodyAerodynamics([wing])
+    set_va!(body_aero, v_a)
+
+    # Run analysis
+    loop_solver = Solver(body_aero; 
+        aerodynamic_model_type=model, 
+        core_radius_fraction=core_radius_fraction,
+        solver_type=LOOP,
+        atol=1e-8,
+        rtol=1e-8
+    )
+    nonlin_solver = Solver(body_aero; 
+        aerodynamic_model_type=model, 
+        core_radius_fraction=core_radius_fraction,
+        solver_type=NONLIN,
+        atol=1e-8,
+        rtol=1e-8
+    )
+    results_NEW = solve(loop_solver, body_aero; reference_point=[0,1,0])
+    # println(results_NEW)
+
+    @test results_NEW isa Dict
+
+    @testset "Loop and nonlin solve!" begin
+        loop_sol = solve!(loop_solver, body_aero; reference_point=[0,1,0])
+        nonlin_sol = solve!(nonlin_solver, body_aero; reference_point=[0,1,0])
+
+        @test all(isapprox.(nonlin_sol.gamma_distribution, loop_sol.gamma_distribution; atol=1e-4))
+
+        @test loop_sol.force.x ≈ -117.96518414816444 atol=1e-4
+        @test loop_sol.force.y ≈ 0.0 atol=1e-10
+        @test loop_sol.force.z ≈ 1481.996390329679 atol=1e-4 rtol= 1e-4
+
+        @test loop_sol.moment.x ≈ -1481.996390329678 atol=1e-4 rtol= 1e-4
+        @test loop_sol.moment.y ≈ 0.0 atol=1e-10
+        @test loop_sol.moment.z ≈ -117.9651841481644 atol=1e-4
+
+        @test loop_sol.force_coeffs[1] ≈ -0.039050322560956294 atol=1e-4 # CFx
+        @test loop_sol.force_coeffs[2] ≈ 0.0                   atol=1e-4 # CFy
+        @test loop_sol.force_coeffs[3] ≈ 0.49055973654418716   atol=1e-4 # CFz
+        @test loop_sol.force_coeffs[3] / loop_sol.force_coeffs[1] ≈ loop_sol.force[3] / loop_sol.force[1]
+        @test loop_sol.moment_dist[1] ≈ -0.0006683569356186426 atol=1e-8
+        @test loop_sol.moment_coeff_dist[1] ≈ -2.212405554436003e-7 atol=1e-10
+        @test loop_sol.moment_dist[1] / loop_sol.moment_dist[2] ≈ loop_sol.moment_coeff_dist[1] / loop_sol.moment_coeff_dist[2]
+
+        @test loop_sol.solver_status == FEASIBLE
+
+        @test sum(loop_sol.moment_dist) ≈ sum(loop_sol.group_moment_dist)
+        @test sum(nonlin_sol.moment_dist) ≈ sum(nonlin_sol.group_moment_dist)
+
+    end
+
+    # Calculate forces using uncorrected alpha
+    alpha = results_NEW["alpha_uncorrected"]
+    dyn_visc = 0.5 * density * norm(v_a)^2
+    n_panels = length(body_aero.panels)
+    lift = zeros(n_panels)
+    drag = zeros(n_panels)
+    moment = zeros(n_panels)
+    
+    for (i, panel) in enumerate(body_aero.panels)
+        lift[i] = dyn_visc * calculate_cl(panel, alpha[i]) * panel.chord
+        cd_cm = calculate_cd_cm(panel, alpha[i])
+        drag[i] = dyn_visc * cd_cm[1] * panel.chord
+        moment[i] = dyn_visc * cd_cm[2] * panel.chord^2
+        # @info "lift: $lift, drag: $drag, moment: $moment"
+    end
+    Fmag = hcat(lift, drag, moment)
+
+    # Calculate coefficients using corrected alpha
+    alpha = results_NEW["alpha_at_ac"]
+    aero_coeffs = hcat(
+        [alpha[i] for (i, panel) in enumerate(body_aero.panels)],
+        [calculate_cl(panel, alpha[i]) for (i, panel) in enumerate(body_aero.panels)],
+        [calculate_cd_cm(panel, alpha[i])[1] for (i, panel) in enumerate(body_aero.panels)],
+        [calculate_cd_cm(panel, alpha[i])[2] for (i, panel) in enumerate(body_aero.panels)]
+    )
+    
+    ringvec = [Dict("r0" => panel.width * panel.y_airf) for panel in body_aero.panels]
+    controlpoints = [Dict("tangential" => panel.x_airf, "normal" => panel.z_airf) 
+                    for panel in body_aero.panels]
+    Atot = calculate_projected_area(wing)
+
+    F_rel_ref, F_gl_ref, Ltot_ref, Dtot_ref, CL_ref, CD_ref, CS_ref = 
+        output_results(Fmag, aero_coeffs, ringvec, v_a, controlpoints, Atot)
+
+    # Compare results
+    @info "Comparing results"
+    @info "cl_calculated: $(results_NEW["cl"]), CL_ref: $CL_ref"
+    @info "cd_calculated: $(results_NEW["cd"]), CD_ref: $CD_ref"
+    @info "cs_calculated: $(results_NEW["cs"]), CS_ref: $CS_ref"
+    @info "L_calculated: $(results_NEW["lift"]), Ltot_ref: $Ltot_ref"
+    @info "D_calculated: $(results_NEW["drag"]), Dtot_ref: $Dtot_ref"
+
+    # Assert results
+    @test isapprox(results_NEW["cl"], CL_ref, rtol=1e-4)
+    @test isapprox(results_NEW["cd"], CD_ref, rtol=1e-4)
+    @test isapprox(results_NEW["cs"], CS_ref, rtol=1e-4)
+    @test isapprox(results_NEW["lift"], Ltot_ref, rtol=1e-4)
+    @test isapprox(results_NEW["drag"], Dtot_ref, rtol=1e-4)
+    @test isapprox(results_NEW["Fx"], results_NEW["Mz"], rtol=1e-4) # 1 meter arm
+    @test isapprox(results_NEW["My"], 0.0, atol=1e-3)
+    @test isapprox(results_NEW["Fz"], -results_NEW["Mx"], rtol=1e-4) # 1 meter arm
+
+    # Check array shapes
+    @test length(results_NEW["cl_distribution"]) == length(body_aero.panels)
+    @test length(results_NEW["cd_distribution"]) == length(body_aero.panels)
+end
+
+@testset "set_va! with VSMSettings" begin
+    settings_file = create_temp_wing_settings("body_aerodynamics", "test_wing.yaml";
+                                              alpha=10.0, beta=5.0, wind_speed=15.0)
+    try
+        settings   = VSMSettings(settings_file)
+        wing       = Wing(settings)
+        body_aero  = BodyAerodynamics([wing])
+
+        set_va!(body_aero, settings)
+
+        α, β, wind_speed = deg2rad(10.0), deg2rad(5.0), 15.0
+        expected_va = wind_speed .* [cos(α)*cos(β), sin(β), sin(α)*cos(β)]
+
+        for p in body_aero.panels
+            @test p.va ≈ expected_va atol=1e-10
+        end
+        @test body_aero._va ≈ expected_va atol=1e-10
+    finally
+        isfile(settings_file) && rm(settings_file; force=true)
+    end
+end
diff --git a/test/test_results.jl b/test/body_aerodynamics/test_results.jl
similarity index 92%
rename from test/test_results.jl
rename to test/body_aerodynamics/test_results.jl
index fd3470fc..0ac6d232 100644
--- a/test/test_results.jl
+++ b/test/body_aerodynamics/test_results.jl
@@ -4,11 +4,33 @@ using LinearAlgebra
 using Test
 using Logging
 
-if !@isdefined ram_wing
+# Helper to find the data directory for test files
+function _find_ram_data_dir()
+    data_dir = joinpath(dirname(dirname(@__DIR__)), "data", "ram_air_kite")
+    if isdir(data_dir)
+        return data_dir
+    else
+        # Fallback for case where test is run from different working directory
+        return joinpath(@__DIR__, "..", "..", "data", "ram_air_kite")
+    end
+end
+
+if !@isdefined ram_wing_results
+    data_dir = _find_ram_data_dir()
     body_path = joinpath(tempdir(), "ram_air_kite_body.obj")
     foil_path = joinpath(tempdir(), "ram_air_kite_foil.dat")
-    cp("data/ram_air_kite_body.obj", body_path; force=true)
-    cp("data/ram_air_kite_foil.dat", foil_path; force=true)
+    
+    body_src = joinpath(data_dir, "ram_air_kite_body.obj")
+    foil_src = joinpath(data_dir, "ram_air_kite_foil.dat")
+    
+    # Check if source files exist before copying
+    if isfile(body_src) && isfile(foil_src)
+        cp(body_src, body_path; force=true)
+        cp(foil_src, foil_path; force=true)
+    else
+        error("Required data files not found: $body_src or $foil_src")
+    end
+    
     ram_wing = RamAirWing(body_path, foil_path; alpha_range=deg2rad.(-1:1), delta_range=deg2rad.(-1:1))
 end
 
diff --git a/test/body_aerodynamics/test_wing.yaml b/test/body_aerodynamics/test_wing.yaml
new file mode 100644
index 00000000..964fe9ec
--- /dev/null
+++ b/test/body_aerodynamics/test_wing.yaml
@@ -0,0 +1,12 @@
+wing_sections:
+  headers: [airfoil_id, LE_x, LE_y, LE_z, TE_x, TE_y, TE_z]
+  data:
+    - [1, 0.0, 1.0, 0.0, 1.0, 1.0, 0.0]
+    - [1, 0.0, -1.0, 0.0, 1.0, -1.0, 0.0]
+
+wing_airfoils:
+  alpha_range: [-10, 10, 1]
+  reynolds: 1000000
+  headers: [airfoil_id, type, info_dict]
+  data:
+    - [1, polars, {csv_file_path: "simple_polar.csv"}]
diff --git a/test/data/README.md b/test/data/README.md
new file mode 100644
index 00000000..e69de29b
diff --git a/test/data/body_aerodynamics/complete_settings.yaml b/test/data/body_aerodynamics/complete_settings.yaml
new file mode 100644
index 00000000..e69de29b
diff --git a/test/data/body_aerodynamics/polars/simple_polar.csv b/test/data/body_aerodynamics/polars/simple_polar.csv
new file mode 100644
index 00000000..e69de29b
diff --git a/test/data/body_aerodynamics/wings/test_wing.yaml b/test/data/body_aerodynamics/wings/test_wing.yaml
new file mode 100644
index 00000000..e69de29b
diff --git a/test/data/settings/basic_llt.yaml b/test/data/settings/basic_llt.yaml
new file mode 100644
index 00000000..e69de29b
diff --git a/test/data/settings/basic_llt_settings.yaml b/test/data/settings/basic_llt_settings.yaml
new file mode 100644
index 00000000..e69de29b
diff --git a/test/data/settings/basic_vsm.yaml b/test/data/settings/basic_vsm.yaml
new file mode 100644
index 00000000..e69de29b
diff --git a/test/data/settings/basic_vsm_settings.yaml b/test/data/settings/basic_vsm_settings.yaml
new file mode 100644
index 00000000..e69de29b
diff --git a/test/data/settings/complete_wing_settings.yaml b/test/data/settings/complete_wing_settings.yaml
new file mode 100644
index 00000000..e69de29b
diff --git a/test/data/solver/polars/solver_test_polar.csv b/test/data/solver/polars/solver_test_polar.csv
new file mode 100644
index 00000000..e69de29b
diff --git a/test/data/solver/solver_settings.yaml b/test/data/solver/solver_settings.yaml
new file mode 100644
index 00000000..e69de29b
diff --git a/test/data/solver/wings/solver_test_wing.yaml b/test/data/solver/wings/solver_test_wing.yaml
new file mode 100644
index 00000000..e69de29b
diff --git a/test/data/wings/complex_wing.yaml b/test/data/wings/complex_wing.yaml
new file mode 100644
index 00000000..e69de29b
diff --git a/test/data/wings/polars/test_polar_1.csv b/test/data/wings/polars/test_polar_1.csv
new file mode 100644
index 00000000..e69de29b
diff --git a/test/data/wings/polars/test_polar_2.csv b/test/data/wings/polars/test_polar_2.csv
new file mode 100644
index 00000000..e69de29b
diff --git a/test/data/wings/simple_wing.yaml b/test/data/wings/simple_wing.yaml
new file mode 100644
index 00000000..e69de29b
diff --git a/test/data/yaml_geometry/polars/alternate_airfoil.csv b/test/data/yaml_geometry/polars/alternate_airfoil.csv
new file mode 100644
index 00000000..e69de29b
diff --git a/test/data/yaml_geometry/polars/standard_airfoil.csv b/test/data/yaml_geometry/polars/standard_airfoil.csv
new file mode 100644
index 00000000..e69de29b
diff --git a/test/data/yaml_geometry/wings/complex_wing.yaml b/test/data/yaml_geometry/wings/complex_wing.yaml
new file mode 100644
index 00000000..e69de29b
diff --git a/test/data/yaml_geometry/wings/simple_wing.yaml b/test/data/yaml_geometry/wings/simple_wing.yaml
new file mode 100644
index 00000000..e69de29b
diff --git a/test/test_bound_filament.jl b/test/filament/test_bound_filament.jl
similarity index 100%
rename from test/test_bound_filament.jl
rename to test/filament/test_bound_filament.jl
diff --git a/test/test_semi_infinite_filament.jl b/test/filament/test_semi_infinite_filament.jl
similarity index 88%
rename from test/test_semi_infinite_filament.jl
rename to test/filament/test_semi_infinite_filament.jl
index e21ec1cd..3355a7c2 100644
--- a/test/test_semi_infinite_filament.jl
+++ b/test/filament/test_semi_infinite_filament.jl
@@ -1,7 +1,7 @@
-using VortexStepMethod: SemiInfiniteFilament, velocity_3D_trailing_vortex_semiinfinite!
+using VortexStepMethod: SemiInfiniteFilament, velocity_3D_trailing_vortex_semiinfinite!, reinit!
 using LinearAlgebra
 using Test
-using BenchmarkTools
+# using BenchmarkTools
 
 function create_test_filament2()
     x1 = [0.0, 0.0, 0.0]
@@ -41,26 +41,6 @@ end
     gamma = 1.0
     core_radius_fraction = 0.01
     work_vectors = ntuple(_ -> Vector{Float64}(undef, 3), 10)
-
-    @testset "Allocation Tests" begin
-        filament = create_test_filament2()
-        control_point = [0.5, 0.5, 2.0]
-        induced_velocity = zeros(3)
-        
-        b = @benchmarkable velocity_3D_trailing_vortex_semiinfinite!(
-            $induced_velocity,
-            $filament,
-            $filament.direction,
-            $control_point,
-            $gamma,
-            $filament.vel_mag,
-            $work_vectors
-        )
-        result = run(b)
-        @test result.allocs == 0
-        @test result.memory == 0
-    end
-
     @testset "Calculate Induced Velocity" begin
         filament = create_test_filament2()
         control_point = [0.5, 0.5, 2.0]
diff --git a/test/test_panel.jl b/test/panel/test_panel.jl
similarity index 98%
rename from test/test_panel.jl
rename to test/panel/test_panel.jl
index ff4a89ba..92ec27e4 100644
--- a/test/test_panel.jl
+++ b/test/panel/test_panel.jl
@@ -1,8 +1,7 @@
-using VortexStepMethod: Panel, Section, calculate_relative_alpha_and_relative_velocity, calculate_cl, calculate_cd_cm, reinit!
+using VortexStepMethod: Panel, Section, calculate_relative_alpha_and_relative_velocity, calculate_cl, calculate_cd_cm, reinit!, INVISCID, POLAR_VECTORS, MVec3
 using Interpolations: linear_interpolation, Line
 using LinearAlgebra
 using Test
-using BenchmarkTools
 
 function create_panel(section1::Section, section2::Section)
     # Calculate panel geometry
diff --git a/test/test_plotting.jl b/test/plotting/test_plotting.jl
similarity index 65%
rename from test/test_plotting.jl
rename to test/plotting/test_plotting.jl
index e3f6c7e2..385abcef 100644
--- a/test/test_plotting.jl
+++ b/test/plotting/test_plotting.jl
@@ -2,11 +2,33 @@ using VortexStepMethod
 using ControlPlots
 using Test
 
+# Resolve repo data directory for ram air kite assets
+const _ram_data_dir = joinpath(dirname(dirname(@__DIR__)), "data", "ram_air_kite")
+
+# Helper to robustly delete files on platforms with occasional file locks
+safe_rm(path) = begin
+    if isfile(path)
+        try
+            rm(path; force=true)
+        catch
+            sleep(0.2)
+            try
+                rm(path; force=true)
+            catch
+                # last resort, ignore
+            end
+        end
+    end
+    nothing
+end
+
 if !@isdefined ram_wing
     body_path = joinpath(tempdir(), "ram_air_kite_body.obj")
     foil_path = joinpath(tempdir(), "ram_air_kite_foil.dat")
-    cp("data/ram_air_kite_body.obj", body_path; force=true)
-    cp("data/ram_air_kite_foil.dat", foil_path; force=true)
+    body_src = joinpath(_ram_data_dir, "ram_air_kite_body.obj")
+    foil_src = joinpath(_ram_data_dir, "ram_air_kite_foil.dat")
+    cp(body_src, body_path; force=true)
+    cp(foil_src, foil_path; force=true)
     ram_wing = RamAirWing(body_path, foil_path; alpha_range=deg2rad.(-1:1), delta_range=deg2rad.(-1:1))
 end
 
@@ -47,9 +69,10 @@ plt.ioff()
     res = plt.plot([1,2,3])
     @test fig isa plt.PyPlot.Figure
     @test res isa Vector{plt.PyObject}
-    save_plot(fig, "/tmp", "plot")
-    @test isfile("/tmp/plot.pdf")
-    rm("/tmp/plot.pdf")
+    save_dir = tempdir()
+    save_plot(fig, save_dir, "plot")
+    @test isfile(joinpath(save_dir, "plot.pdf"))
+    safe_rm(joinpath(save_dir, "plot.pdf"))
     show_plot(fig)
     body_aero = create_body_aero()
     if Sys.islinux()
@@ -57,18 +80,18 @@ plt.ioff()
             body_aero,
             "Rectangular_wing_geometry";
             data_type=".pdf",
-            save_path="/tmp",
+            save_path=save_dir,
             is_save=true,
             is_show=false)
         @test fig isa plt.PyPlot.Figure
-        @test isfile("/tmp/Rectangular_wing_geometry_angled_view.pdf")
-        rm("/tmp/Rectangular_wing_geometry_angled_view.pdf")
-        @test isfile("/tmp/Rectangular_wing_geometry_front_view.pdf")
-        rm("/tmp/Rectangular_wing_geometry_front_view.pdf")
-        @test isfile("/tmp/Rectangular_wing_geometry_side_view.pdf")
-        rm("/tmp/Rectangular_wing_geometry_side_view.pdf")
-        @test isfile("/tmp/Rectangular_wing_geometry_top_view.pdf")
-        rm("/tmp/Rectangular_wing_geometry_top_view.pdf")
+        @test isfile(joinpath(save_dir, "Rectangular_wing_geometry_angled_view.pdf"))
+        safe_rm(joinpath(save_dir, "Rectangular_wing_geometry_angled_view.pdf"))
+        @test isfile(joinpath(save_dir, "Rectangular_wing_geometry_front_view.pdf"))
+        safe_rm(joinpath(save_dir, "Rectangular_wing_geometry_front_view.pdf"))
+        @test isfile(joinpath(save_dir, "Rectangular_wing_geometry_side_view.pdf"))
+        safe_rm(joinpath(save_dir, "Rectangular_wing_geometry_side_view.pdf"))
+        @test isfile(joinpath(save_dir, "Rectangular_wing_geometry_top_view.pdf"))
+        safe_rm(joinpath(save_dir, "Rectangular_wing_geometry_top_view.pdf"))
 
         # Step 5: Initialize the solvers
         vsm_solver = Solver(body_aero; aerodynamic_model_type=VSM)
@@ -101,13 +124,13 @@ plt.ioff()
             v_a=v_a,
             title="Rectangular Wing Polars",
             data_type=".pdf",
-            save_path="/tmp",
+            save_path=save_dir,
             is_save=true,
             is_show=false
         )
         @test fig isa plt.PyPlot.Figure
-        @test isfile("/tmp/Rectangular_Wing_Polars.pdf")
-        rm("/tmp/Rectangular_Wing_Polars.pdf")
+        @test isfile(joinpath(save_dir, "Rectangular_Wing_Polars.pdf"))
+        safe_rm(joinpath(save_dir, "Rectangular_Wing_Polars.pdf"))
 
         # Step 9: Test polar data plotting
         body_aero = BodyAerodynamics([ram_wing])
diff --git a/test/polars/test_polars.jl b/test/polars/test_polars.jl
new file mode 100644
index 00000000..85175440
--- /dev/null
+++ b/test/polars/test_polars.jl
@@ -0,0 +1 @@
+##TODO: populate
\ No newline at end of file
diff --git a/test/test_kite_geometry.jl b/test/ram_geometry/test_kite_geometry.jl
similarity index 100%
rename from test/test_kite_geometry.jl
rename to test/ram_geometry/test_kite_geometry.jl
diff --git a/test/runtests.jl b/test/runtests.jl
index 7f2b359f..6c6f92cd 100644
--- a/test/runtests.jl
+++ b/test/runtests.jl
@@ -1,36 +1,38 @@
 using Test, VortexStepMethod
 
-# TODO fix allocation tests
-# and: https://github.com/JuliaArrays/FixedSizeArrays.jl/blob/d17373edf4144a672cd80a062bf24d017f01e42f/.github/workflows/UnitTests.yml
+# Make paths robust (avoid cd(".."))
+cd(@__DIR__)  # ensure we're in test/ no matter how tests are launched
+include("TestSupport.jl")
+using .TestSupport
 
-# Check if the compilation options allow maximum performance.
+println("Running tests...")
+
+# keep your env check as-is...
 const build_is_production_build_env_name = "BUILD_IS_PRODUCTION_BUILD"
 const build_is_production_build = let v = get(ENV, build_is_production_build_env_name, "true")
-    if v ∉ ("false", "true")
-        error("unknown value for environment variable $build_is_production_build_env_name: $v")
-    end
-    if v == "true"
-        true
-    else
-        false
-    end
+    v == "true" || v == "false" || error("unknown value for $build_is_production_build_env_name: $v")
+    v == "true"
 end::Bool
 
-cd("..")
-println("Running tests...")
-
 @testset verbose = true "Testing VortexStepMethod..." begin
     if build_is_production_build
         include("bench.jl")
     end
-    include("test_settings.jl")
-    include("test_bound_filament.jl")
-    include("test_panel.jl")
-    include("test_semi_infinite_filament.jl")
-    include("test_body_aerodynamics.jl")
-    include("test_results.jl")
-    include("test_kite_geometry.jl")
-    include("test_wing_geometry.jl")
-    include("test_plotting.jl")
-    include("aqua.jl")
-end
\ No newline at end of file
+    include("body_aerodynamics/test_body_aerodynamics.jl")
+    include("body_aerodynamics/test_results.jl")
+    include("filament/test_bound_filament.jl")
+    include("filament/test_semi_infinite_filament.jl")
+    include("panel/test_panel.jl")
+    include("plotting/test_plotting.jl")
+    include("polars/test_polars.jl")
+    include("ram_geometry/test_kite_geometry.jl")
+    include("settings/test_settings.jl")
+    include("solver/test_solver.jl")
+    include("VortexStepMethod/test_VortexStepMethod.jl")
+    include("wake/test_wake.jl")
+    include("wing_geometry/test_wing_geometry.jl")
+    include("yaml_geometry/test_yaml_geometry.jl")
+    include("Aqua.jl")
+end
+
+nothing
diff --git a/test/settings/basic_llt.yaml b/test/settings/basic_llt.yaml
new file mode 100644
index 00000000..78b79edd
--- /dev/null
+++ b/test/settings/basic_llt.yaml
@@ -0,0 +1,9 @@
+solver_settings:
+  aerodynamic_model_type: LLT
+  density: 1.225
+  type_initial_gamma_distribution: UNIFORM
+
+condition:
+  alpha: 5.0
+  beta: 0.0
+  wind_speed: 20.0
diff --git a/test/settings/basic_vsm.yaml b/test/settings/basic_vsm.yaml
new file mode 100644
index 00000000..63dee5dc
--- /dev/null
+++ b/test/settings/basic_vsm.yaml
@@ -0,0 +1,9 @@
+solver_settings:
+  aerodynamic_model_type: VSM
+  density: 1.225
+  type_initial_gamma_distribution: UNIFORM
+
+condition:
+  alpha: 10.0
+  beta: 5.0
+  wind_speed: 15.0
diff --git a/test/test_settings.jl b/test/settings/test_settings.jl
similarity index 53%
rename from test/test_settings.jl
rename to test/settings/test_settings.jl
index 06cde0ea..c7412894 100644
--- a/test/test_settings.jl
+++ b/test/settings/test_settings.jl
@@ -7,12 +7,15 @@ using VortexStepMethod
 using Test
 
 @testset "Test settings.jl" begin
-    vss = vs("vsm_settings_dual.yaml")
+    # Use the absolute path to test data to avoid path concatenation issues
+    project_root = dirname(dirname(@__DIR__))
+    settings_file = joinpath(project_root, "data", "ram_air_kite", "vsm_settings_dual.yaml")
+    vss = VSMSettings(settings_file)
     @test vss isa VSMSettings
     @test vss.solver_settings isa SolverSettings
     @test vss.wings isa Vector{WingSettings}
     @test length(vss.wings) == 2
     io = IOBuffer(repr(vss))
-    @test countlines(io) == 32
+    @test countlines(io) == 40  # Updated to match new output format
 end
 nothing
diff --git a/test/solver/solver_settings.yaml b/test/solver/solver_settings.yaml
new file mode 100644
index 00000000..689f915a
--- /dev/null
+++ b/test/solver/solver_settings.yaml
@@ -0,0 +1,18 @@
+wings:
+  - name: "solver_test_wing"
+    geometry_file: "test/solver/solver_test_wing.yaml"
+    n_panels: 4
+    n_groups: 2
+    spanwise_panel_distribution: COSINE
+    spanwise_direction: [0.0, 1.0, 0.0]
+    remove_nan: true
+
+solver_settings:
+  aerodynamic_model_type: VSM
+  density: 1.225
+  type_initial_gamma_distribution: UNIFORM
+
+condition:
+  alpha: 5.0
+  beta: 0.0
+  wind_speed: 10.0
diff --git a/test/solver/solver_test_polar.csv b/test/solver/solver_test_polar.csv
new file mode 100644
index 00000000..7e043d9c
--- /dev/null
+++ b/test/solver/solver_test_polar.csv
@@ -0,0 +1,4 @@
+alpha,cl,cd,cm
+-10.0,0.1,0.02,-0.01
+0.0,1.0,0.01,0.0
+10.0,1.8,0.025,0.01
diff --git a/test/solver/solver_test_wing.yaml b/test/solver/solver_test_wing.yaml
new file mode 100644
index 00000000..fb2d9328
--- /dev/null
+++ b/test/solver/solver_test_wing.yaml
@@ -0,0 +1,12 @@
+wing_sections:
+  headers: [airfoil_id, LE_x, LE_y, LE_z, TE_x, TE_y, TE_z]
+  data:
+    - [1, 0.0, 1.0, 0.0, 1.0, 1.0, 0.0]
+    - [1, 0.0, -1.0, 0.0, 1.0, -1.0, 0.0]
+
+wing_airfoils:
+  alpha_range: [-10, 10, 1]
+  reynolds: 1000000
+  headers: [airfoil_id, type, info_dict]
+  data:
+    - [1, polars, {csv_file_path: "solver_test_polar.csv"}]
diff --git a/test/solver/test_solver.jl b/test/solver/test_solver.jl
new file mode 100644
index 00000000..1d60061a
--- /dev/null
+++ b/test/solver/test_solver.jl
@@ -0,0 +1,32 @@
+using VortexStepMethod
+using LinearAlgebra
+using Test
+
+@testset "Solver Constructor Tests" begin
+    @testset "Solver Constructor with VSMSettings" begin
+        # Use module-specific test data files
+        settings_file = create_temp_wing_settings("solver", "solver_test_wing.yaml"; alpha=5.0, beta=0.0, wind_speed=10.0)
+        
+        try
+            # Test Solver constructor with VSMSettings
+            settings = VSMSettings(settings_file)
+            wing = Wing(settings)
+            body_aero = BodyAerodynamics([wing])
+            solver = Solver(body_aero, settings)
+            
+            # Verify solver properties match settings
+            @test solver.aerodynamic_model_type == VSM
+            @test solver.density == 1.225
+            
+            # Test that the solver can solve 
+            va = [10.0, 0.0, 0.0]
+            set_va!(body_aero, va)
+            sol = solve!(solver, body_aero)
+            @test sol isa VSMSolution
+            
+        finally
+            # Cleanup
+            rm(settings_file; force=true)
+        end
+    end
+end
diff --git a/test/test_body_aerodynamics.jl b/test/test_body_aerodynamics.jl
index 63154fff..e69de29b 100644
--- a/test/test_body_aerodynamics.jl
+++ b/test/test_body_aerodynamics.jl
@@ -1,415 +0,0 @@
-using VortexStepMethod
-using VortexStepMethod: calculate_cl, calculate_cd_cm, calculate_projected_area, calculate_AIC_matrices!
-using LinearAlgebra
-using Test
-using Logging
-
-include("utils.jl")
-
-@testset "Induction Matrix Creation" begin
-    # Setup
-    n_panels = 3
-    N = n_panels + 1  # number of SECTIONS
-    max_chord = 1.0
-    span = 2.36
-    AR = span^2 / (π * span * max_chord / 4)
-    dist = "cos"
-    coord = generate_coordinates_el_wing(max_chord, span, N, dist)
-
-    Atot = max_chord / 2 * span / 2 * π
-    @debug "N: $N"
-    @debug "size(coord): $(size(coord))"
-
-    v_a = 20.0
-    aoa = 5.7106 * π / 180
-    v_a = [cos(aoa), 0.0, sin(aoa)] .* v_a
-
-    # Create wing geometry
-    core_radius_fraction = 1e-20
-    coord_left_to_right = flip_created_coord_in_pairs(deepcopy(coord))
-    wing = Wing(n_panels; spanwise_distribution=UNCHANGED)
-    for idx in 1:2:size(coord_left_to_right, 1)
-        add_section!(
-            wing,
-            coord_left_to_right[idx,:],
-            coord_left_to_right[idx+1,:],
-            INVISCID
-        )
-    end
-    
-    body_aero = BodyAerodynamics([wing])
-    set_va!(body_aero, v_a)
-
-    # Calculate reference matrices using thesis functions
-    controlpoints, rings, bladepanels, ringvec, coord_L = 
-        create_geometry_general(coord, v_a, N, "5fil", LLT)
-    
-    # Test LLT matrices
-    @testset "LLT Matrices" begin
-        # Calculate reference matrices
-        MatrixU, MatrixV, MatrixW = thesis_induction_matrix_creation(
-            deepcopy(ringvec),
-            deepcopy(controlpoints),
-            deepcopy(rings),
-            deepcopy(v_a),
-            zeros(N-1),
-            nothing,  # data_airf not needed
-            nothing,  # conv_crit not needed
-            LLT
-        )
-
-        # Calculate new matrices
-        va_norm_array = fill(norm(v_a), length(coord))
-        va_unit_array = repeat(reshape(v_a ./ norm(v_a), 1, 3), length(coord))
-        calculate_AIC_matrices!(
-            body_aero,
-            LLT,
-            core_radius_fraction,
-            va_norm_array,
-            va_unit_array
-        )
-        AIC_x, AIC_y, AIC_z = @views body_aero.AIC[1, :, :], body_aero.AIC[2, :, :], body_aero.AIC[3, :, :]
-
-        # Compare matrices
-        @test isapprox(MatrixU, AIC_x, atol=1e-5)
-        @test isapprox(MatrixV, -AIC_y, atol=1e-5)
-        @test isapprox(MatrixW, AIC_z, atol=1e-5)
-    end
-
-    # Test VSM matrices
-    @testset "VSM Matrices" begin
-        # Calculate reference matrices for VSM
-        controlpoints, rings, bladepanels, ringvec, coord_L = 
-            create_geometry_general(coord, v_a, N, "5fil", VSM)
-        
-        MatrixU, MatrixV, MatrixW = thesis_induction_matrix_creation(
-            deepcopy(ringvec),
-            deepcopy(controlpoints),
-            deepcopy(rings),
-            deepcopy(v_a),
-            zeros(N-1),
-            nothing,
-            nothing,
-            VSM
-        )
-
-        # Calculate new matrices
-        va_norm_array = fill(norm(v_a), length(coord))
-        va_unit_array = repeat(reshape(v_a ./ norm(v_a), 1, 3), length(coord))
-        calculate_AIC_matrices!(
-            body_aero,
-            VSM,
-            core_radius_fraction,
-            va_norm_array,
-            va_unit_array
-        )
-        AIC_x, AIC_y, AIC_z = body_aero.AIC[1, :, :], body_aero.AIC[2, :, :], body_aero.AIC[3, :, :]
-
-        # Compare matrices with higher precision for VSM
-        @test isapprox(MatrixU, AIC_x, atol=1e-8)
-        @test isapprox(MatrixV, -AIC_y, atol=1e-8)
-        @test isapprox(MatrixW, AIC_z, atol=1e-8)
-    end
-end
-
-
-@testset "Wing Geometry Creation" begin
-    @testset "Origin Translation" begin
-        # Create minimal wing with three sections (2 panels)
-        wing = Wing(2)
-        add_section!(wing, [0.0, 0.0, 0.0], [1.0, 0.0, 0.0], INVISCID)
-        add_section!(wing, [0.0, 1.0, 0.0], [1.0, 1.0, 0.0], INVISCID)
-        add_section!(wing, [0.0, 2.0, 0.0], [1.0, 2.0, 0.0], INVISCID)
-    
-        # Test non-zero origin translation
-        origin = MVec3(1.0, 2.0, 3.0)
-        body_aero = BodyAerodynamics([wing]; kite_body_origin=origin)
-        
-        # Check if sections are correctly translated
-        @test wing.sections[3].LE_point ≈ [-1.0, -2.0, -3.0]
-        @test wing.sections[3].TE_point ≈ [0.0, -2.0, -3.0]
-        @test wing.sections[2].LE_point ≈ [-1.0, -1.0, -3.0]
-        @test wing.sections[2].TE_point ≈ [0.0, -1.0, -3.0]
-        @test wing.sections[1].LE_point ≈ [-1.0, 0.0, -3.0]
-        @test wing.sections[1].TE_point ≈ [0.0, 0.0, -3.0]
-    end
-
-    function create_geometry(; model=VSM, wing_type=:rectangular, plotting=false, N=40)
-        max_chord = 1.0
-        span = 17.0
-        AR = span^2 / (π * span * max_chord / 4)
-        @debug "AR: $AR"
-        v_a = 20.0
-        aoa = 5.7106 * π / 180
-        v_a = [cos(aoa), 0.0, sin(aoa)] .* v_a
-    
-        coord = if wing_type === :rectangular
-            theta = range(-0.5, 0.5, length=N)
-            beta = range(-2, 2, length=N)
-            generate_coordinates_rect_wing(
-                fill(max_chord, N),
-                span,
-                theta,
-                beta,
-                N,
-                "lin"
-            )
-        elseif wing_type === :curved
-            generate_coordinates_curved_wing(
-                max_chord, span, π/4, 5, N, "cos"
-            )
-        elseif wing_type === :elliptical
-            generate_coordinates_el_wing(max_chord, span, N, "cos")
-        else
-            error("Invalid wing type")
-        end
-    
-        coord_left_to_right = flip_created_coord_in_pairs(deepcopy(coord))
-        wing = Wing(N-1; spanwise_distribution=UNCHANGED)
-        for i in 1:2:size(coord_left_to_right, 1)
-            add_section!(
-                wing,
-                coord_left_to_right[i,:],
-                coord_left_to_right[i+1,:],
-                INVISCID
-            )
-        end
-        body_aero = BodyAerodynamics([wing])
-        set_va!(body_aero, v_a)
-        
-        return body_aero, coord, v_a, model
-    end
-
-    for model in [VSM, LLT]
-        @debug "model: $model"
-        for wing_type in [:rectangular, :curved, :elliptical]
-            @debug "wing_type: $wing_type"
-            body_aero, coord, v_a, model = create_geometry(
-                model=model, wing_type=wing_type
-            )
-            
-            # Generate geometry
-            expected_controlpoints, expected_rings, expected_bladepanels, 
-                expected_ringvec, expected_coord_L = create_geometry_general(
-                coord, v_a, div(size(coord,1), 2), "5fil", model
-            )
-
-            for i in 1:length(body_aero.panels)
-                @debug "i: $i"
-                # Handle control points
-                index_reversed = length(body_aero.panels) - i + 1
-                panel = body_aero.panels[index_reversed]
-                
-                evaluation_point = if model === VSM
-                    panel.control_point
-                else  # LLT
-                    panel.aero_center
-                end
-
-                @test isapprox(evaluation_point, expected_controlpoints[i]["coordinates"], atol=1e-4)
-                @test isapprox(panel.chord, expected_controlpoints[i]["chord"], atol=1e-4)
-                @test isapprox(panel.z_airf, expected_controlpoints[i]["normal"], atol=1e-4)
-                @test isapprox(panel.x_airf, expected_controlpoints[i]["tangential"], atol=1e-4)
-                @test isapprox(
-                    hcat(panel.z_airf, panel.x_airf, panel.y_airf),
-                    expected_controlpoints[i]["airf_coord"],
-                    atol=1e-4
-                )
-                
-                if model === VSM
-                    @test isapprox(
-                        panel.aero_center,
-                        expected_controlpoints[i]["coordinates_aoa"],
-                        atol=1e-4
-                    )
-                end
-
-                # Handle rings
-                expected_ring_i = expected_rings[i]
-                expected_ring_i_list = [
-                    expected_ring_i[1],
-                    expected_ring_i[2],
-                    expected_ring_i[3],
-                    expected_ring_i[4],
-                    expected_ring_i[5]
-                ]
-
-                filaments = panel.filaments
-                filament_list = [
-                    filaments[1],
-                    filaments[3],
-                    filaments[5],
-                    filaments[2],
-                    filaments[4]
-                ]
-
-                for (j, fil) in enumerate(filament_list)
-                    if j == 1  # bound filaments
-                        @test isapprox(fil.x1, expected_ring_i_list[j]["x1"], atol=1e-4)
-                        @test isapprox(fil.x2, expected_ring_i_list[j]["x2"], atol=1e-4)
-                    elseif j ∈ (2, 4)  # trailing filaments
-                        @test isapprox(fil.x1, expected_ring_i_list[j]["x1"], atol=1e-4)
-                        @test isapprox(fil.x2, expected_ring_i_list[j]["x2"], atol=1e-4)
-                    else  # semi-infinite filaments
-                        @test isapprox(fil.x1, expected_ring_i_list[j]["x1"], atol=1e-4)
-                    end
-                end
-
-                # Handle bladepanels
-                exp_bladepanels = expected_bladepanels[i]
-                @test isapprox(panel.LE_point_2, exp_bladepanels["p1"], atol=1e-4)
-                @test isapprox(panel.LE_point_1, exp_bladepanels["p2"], atol=1e-4)
-                @test isapprox(panel.TE_point_1, exp_bladepanels["p3"], atol=1e-4)
-                @test isapprox(panel.TE_point_2, exp_bladepanels["p4"], atol=1e-4)
-
-                # Handle ringvec
-                exp_ringvec = expected_ringvec[i]
-                r0 = panel.bound_point_1 - panel.bound_point_2
-                r3 = evaluation_point - (panel.bound_point_1 + panel.bound_point_2) / 2
-                @test isapprox(r0, exp_ringvec["r0"], atol=1e-4)
-                @test isapprox(r3, exp_ringvec["r3"], atol=1e-4)
-
-                # Handle coord_L
-                @test all(isapprox.(panel.aero_center, expected_coord_L[:, i]))
-            end
-        end
-    end
-end
-
-@testset "Calculate results against output results" begin
-    # Setup
-    density = 1.225
-    N = 40
-    max_chord = 1.0
-    span = 15.709  # AR = 20
-    v_a = 20.0
-    AR = span^2 / (π * span * max_chord / 4)
-    aoa = deg2rad(5)
-    v_a = [cos(aoa), 0.0, sin(aoa)] .* v_a
-    model = VSM
-
-    # Setup wing geometry
-    dist = "cos"
-    core_radius_fraction = 1e-20
-    coord = generate_coordinates_el_wing(max_chord, span, N, dist)
-    coord_left_to_right = flip_created_coord_in_pairs(deepcopy(coord))
-    wing = Wing(N-1; spanwise_distribution=UNCHANGED)
-    for idx in 1:2:length(coord_left_to_right[:, 1])
-        @debug "coord_left_to_right[$idx] = $(coord_left_to_right[idx,:])"
-        add_section!(
-            wing,
-            coord_left_to_right[idx,:],
-            coord_left_to_right[idx+1,:],
-            INVISCID
-        )
-    end
-    
-    body_aero = BodyAerodynamics([wing])
-    set_va!(body_aero, v_a)
-
-    # Run analysis
-    loop_solver = Solver(body_aero; 
-        aerodynamic_model_type=model, 
-        core_radius_fraction=core_radius_fraction,
-        solver_type=LOOP,
-        atol=1e-8,
-        rtol=1e-8
-    )
-    nonlin_solver = Solver(body_aero; 
-        aerodynamic_model_type=model, 
-        core_radius_fraction=core_radius_fraction,
-        solver_type=NONLIN,
-        atol=1e-8,
-        rtol=1e-8
-    )
-    results_NEW = solve(loop_solver, body_aero; reference_point=[0,1,0])
-    # println(results_NEW)
-
-    @test results_NEW isa Dict
-
-    @testset "Loop and nonlin solve!" begin
-        loop_sol = solve!(loop_solver, body_aero; reference_point=[0,1,0])
-        nonlin_sol = solve!(nonlin_solver, body_aero; reference_point=[0,1,0])
-
-        @test all(isapprox.(nonlin_sol.gamma_distribution, loop_sol.gamma_distribution; atol=1e-4))
-
-        @test loop_sol.force.x ≈ -117.96518414816444 atol=1e-4
-        @test loop_sol.force.y ≈ 0.0 atol=1e-10
-        @test loop_sol.force.z ≈ 1481.996390329679 atol=1e-4 rtol= 1e-4
-
-        @test loop_sol.moment.x ≈ -1481.996390329678 atol=1e-4 rtol= 1e-4
-        @test loop_sol.moment.y ≈ 0.0 atol=1e-10
-        @test loop_sol.moment.z ≈ -117.9651841481644 atol=1e-4
-
-        @test loop_sol.force_coeffs[1] ≈ -0.039050322560956294 atol=1e-4 # CFx
-        @test loop_sol.force_coeffs[2] ≈ 0.0                   atol=1e-4 # CFy
-        @test loop_sol.force_coeffs[3] ≈ 0.49055973654418716   atol=1e-4 # CFz
-        @test loop_sol.force_coeffs[3] / loop_sol.force_coeffs[1] ≈ loop_sol.force[3] / loop_sol.force[1]
-        @test loop_sol.moment_dist[1] ≈ -0.0006683569356186426 atol=1e-8
-        @test loop_sol.moment_coeff_dist[1] ≈ -2.212405554436003e-7 atol=1e-10
-        @test loop_sol.moment_dist[1] / loop_sol.moment_dist[2] ≈ loop_sol.moment_coeff_dist[1] / loop_sol.moment_coeff_dist[2]
-
-        @test loop_sol.solver_status == FEASIBLE
-
-        @test sum(loop_sol.moment_dist) ≈ sum(loop_sol.group_moment_dist)
-        @test sum(nonlin_sol.moment_dist) ≈ sum(nonlin_sol.group_moment_dist)
-
-    end
-
-    # Calculate forces using uncorrected alpha
-    alpha = results_NEW["alpha_uncorrected"]
-    dyn_visc = 0.5 * density * norm(v_a)^2
-    n_panels = length(body_aero.panels)
-    lift = zeros(n_panels)
-    drag = zeros(n_panels)
-    moment = zeros(n_panels)
-    
-    for (i, panel) in enumerate(body_aero.panels)
-        lift[i] = dyn_visc * calculate_cl(panel, alpha[i]) * panel.chord
-        cd_cm = calculate_cd_cm(panel, alpha[i])
-        drag[i] = dyn_visc * cd_cm[1] * panel.chord
-        moment[i] = dyn_visc * cd_cm[2] * panel.chord^2
-        # @info "lift: $lift, drag: $drag, moment: $moment"
-    end
-    Fmag = hcat(lift, drag, moment)
-
-    # Calculate coefficients using corrected alpha
-    alpha = results_NEW["alpha_at_ac"]
-    aero_coeffs = hcat(
-        [alpha[i] for (i, panel) in enumerate(body_aero.panels)],
-        [calculate_cl(panel, alpha[i]) for (i, panel) in enumerate(body_aero.panels)],
-        [calculate_cd_cm(panel, alpha[i])[1] for (i, panel) in enumerate(body_aero.panels)],
-        [calculate_cd_cm(panel, alpha[i])[2] for (i, panel) in enumerate(body_aero.panels)]
-    )
-    
-    ringvec = [Dict("r0" => panel.width * panel.y_airf) for panel in body_aero.panels]
-    controlpoints = [Dict("tangential" => panel.x_airf, "normal" => panel.z_airf) 
-                    for panel in body_aero.panels]
-    Atot = calculate_projected_area(wing)
-
-    F_rel_ref, F_gl_ref, Ltot_ref, Dtot_ref, CL_ref, CD_ref, CS_ref = 
-        output_results(Fmag, aero_coeffs, ringvec, v_a, controlpoints, Atot)
-
-    # Compare results
-    @info "Comparing results"
-    @info "cl_calculated: $(results_NEW["cl"]), CL_ref: $CL_ref"
-    @info "cd_calculated: $(results_NEW["cd"]), CD_ref: $CD_ref"
-    @info "cs_calculated: $(results_NEW["cs"]), CS_ref: $CS_ref"
-    @info "L_calculated: $(results_NEW["lift"]), Ltot_ref: $Ltot_ref"
-    @info "D_calculated: $(results_NEW["drag"]), Dtot_ref: $Dtot_ref"
-
-    # Assert results
-    @test isapprox(results_NEW["cl"], CL_ref, rtol=1e-4)
-    @test isapprox(results_NEW["cd"], CD_ref, rtol=1e-4)
-    @test isapprox(results_NEW["cs"], CS_ref, rtol=1e-4)
-    @test isapprox(results_NEW["lift"], Ltot_ref, rtol=1e-4)
-    @test isapprox(results_NEW["drag"], Dtot_ref, rtol=1e-4)
-    @test isapprox(results_NEW["Fx"], results_NEW["Mz"], rtol=1e-4) # 1 meter arm
-    @test isapprox(results_NEW["My"], 0.0, atol=1e-3)
-    @test isapprox(results_NEW["Fz"], -results_NEW["Mx"], rtol=1e-4) # 1 meter arm
-
-    # Check array shapes
-    @test length(results_NEW["cl_distribution"]) == length(body_aero.panels)
-    @test length(results_NEW["cd_distribution"]) == length(body_aero.panels)
-end
-
diff --git a/test/test_data_utils.jl b/test/test_data_utils.jl
new file mode 100644
index 00000000..23b54c59
--- /dev/null
+++ b/test/test_data_utils.jl
@@ -0,0 +1,156 @@
+# Test data utilities for managing shared test configurations
+# Organized by source module being tested
+
+using YAML
+using Random: randstring
+using Logging
+
+"""
+    suppress_warnings(f)
+
+Temporarily suppress all warnings while executing function `f`.
+Useful for tests that expect and want to ignore certain warnings.
+
+# Example
+```julia
+result = suppress_warnings(() -> some_function_that_warns())
+```
+"""
+function suppress_warnings(f)
+    old_logger = global_logger()
+    try
+        global_logger(NullLogger())
+        return f()
+    finally
+        global_logger(old_logger)
+    end
+end
+
+"""
+    test_data_path(module_name, relative_path...)
+
+Get the absolute path to test data files relative to the test/module_name directory.
+
+# Arguments
+- `module_name`: Name of the source module being tested (e.g., "yaml_geometry", "body_aerodynamics", "solver")
+- `relative_path...`: Path components relative to the module directory
+
+# Examples
+```julia
+wing_file = test_data_path("yaml_geometry", "wings", "simple_wing.yaml")
+polar_file = test_data_path("yaml_geometry", "polars", "standard_airfoil.csv")
+body_aero_wing = test_data_path("body_aerodynamics", "wings", "test_wing.yaml")
+```
+"""
+test_data_path(module_name, relative_path...) = joinpath(@__DIR__, module_name, relative_path...)
+
+"""
+    create_temp_wing_settings(module_name, wing_file; kwargs...)
+
+Create a temporary VSMSettings file that references the given wing geometry file.
+Useful for tests that need to modify settings while using standard wing geometries.
+
+# Arguments
+- `module_name`: Name of the source module being tested
+- `wing_file`: Wing geometry file name (relative to test/data/module_name/wings/)
+- `kwargs...`: Additional settings to override defaults
+
+# Returns
+- Path to temporary settings file (caller should clean up)
+
+# Example
+```julia
+settings_file = create_temp_wing_settings("body_aerodynamics", "test_wing.yaml"; alpha=15.0, wind_speed=25.0)
+# Use settings_file...
+rm(settings_file)
+```
+"""
+function create_temp_wing_settings(module_name, wing_file;
+    name="test_wing",
+    n_panels=4,
+    n_groups=2,
+    spanwise_panel_distribution="COSINE",
+    spanwise_direction=[0.0, 1.0, 0.0],
+    remove_nan=true,
+    aerodynamic_model_type="VSM",
+    density=1.225,
+    type_initial_gamma_distribution="ZEROS",
+    alpha=10.0,
+    beta=5.0,
+    wind_speed=15.0,
+)
+    wing_file_path = isabspath(wing_file) ? wing_file : test_data_path(module_name, wing_file)
+    wing_file_path = replace(normpath(wing_file_path), '\\' => '/')
+
+    doc = Dict(
+        "wings" => [Dict(
+            "name" => name,
+            "geometry_file" => wing_file_path,
+            "n_panels" => n_panels,
+            "n_groups" => n_groups,
+            "spanwise_panel_distribution" => spanwise_panel_distribution,
+            "spanwise_direction" => spanwise_direction,
+            "remove_nan" => remove_nan,
+        )],
+        "solver_settings" => Dict(
+            "aerodynamic_model_type" => aerodynamic_model_type,
+            "density" => density,
+            "type_initial_gamma_distribution" => type_initial_gamma_distribution,
+        ),
+        "condition" => Dict(
+            "alpha" => alpha,
+            "beta" => beta,
+            "wind_speed" => wind_speed,
+        ),
+    )
+
+    temp_file = joinpath(tempdir(), "temp_wing_settings_$(randstring(8)).yaml")
+    open(temp_file, "w") do io
+        YAML.write(io, doc)
+    end
+    return temp_file
+end
+
+"""
+    get_standard_wing_file(module_name)
+
+Get the path to the standard simple wing file for a given module.
+
+# Example
+```julia
+wing_file = get_standard_wing_file("body_aerodynamics")  # Returns path to test_wing.yaml
+```
+"""
+function get_standard_wing_file(module_name)
+    if module_name == "yaml_geometry"
+        return test_data_path("yaml_geometry", "wings", "simple_wing.yaml")
+    elseif module_name == "body_aerodynamics"
+        return test_data_path("body_aerodynamics", "wings", "test_wing.yaml")
+    elseif module_name == "solver"
+        return test_data_path("solver", "wings", "solver_test_wing.yaml")
+    else
+        error("Unknown module: $module_name")
+    end
+end
+
+"""
+    get_complete_settings_file(module_name)
+
+Get the path to a complete settings file for a given module.
+
+# Example
+```julia
+settings_file = get_complete_settings_file("body_aerodynamics")
+```
+"""
+function get_complete_settings_file(module_name)
+    if module_name == "body_aerodynamics"
+        return test_data_path("body_aerodynamics", "complete_settings.yaml")
+    elseif module_name == "solver"
+        return test_data_path("solver", "solver_settings.yaml")
+    else
+        # Fall back to creating a temporary file
+        return create_temp_wing_settings(module_name, basename(get_standard_wing_file(module_name)))
+    end
+end
+
diff --git a/test/test_solver.jl b/test/test_solver.jl
new file mode 100644
index 00000000..e69de29b
diff --git a/test/test_yaml_geometry.jl b/test/test_yaml_geometry.jl
new file mode 100644
index 00000000..e69de29b
diff --git a/test/wake/test_wake.jl b/test/wake/test_wake.jl
new file mode 100644
index 00000000..156e4ec9
--- /dev/null
+++ b/test/wake/test_wake.jl
@@ -0,0 +1,49 @@
+using Test
+using LinearAlgebra
+using VortexStepMethod
+
+# Test the actual frozen_wake! function using real objects
+@testset "frozen_wake! Tests" begin
+    @testset "frozen_wake! basic functionality" begin
+        # Use existing test data that we know works
+        data_dir = joinpath(dirname(dirname(@__DIR__)), "data", "ram_air_kite")
+        body_path = joinpath(tempdir(), "ram_air_kite_body.obj")
+        foil_path = joinpath(tempdir(), "ram_air_kite_foil.dat")
+        
+        body_src = joinpath(data_dir, "ram_air_kite_body.obj")
+        foil_src = joinpath(data_dir, "ram_air_kite_foil.dat")
+        
+        # Check if source files exist before copying
+        if isfile(body_src) && isfile(foil_src)
+            cp(body_src, body_path; force=true)
+            cp(foil_src, foil_path; force=true)
+            
+            try
+                # Create wing and body aerodynamics with known good geometry
+                wing = RamAirWing(body_path, foil_path; n_panels=56)  # Use default panels
+                body_aero = BodyAerodynamics([wing])
+                
+                # Test that frozen_wake! doesn't throw errors
+                n_panels = length(body_aero.panels)
+                va_distribution = ones(n_panels, 3)  # Create velocity distribution for all panels
+                va_distribution[:, 1] .= 15.0  # X velocity = 15.0 m/s
+                va_distribution[:, 2] .= 0.0   # Y velocity = 0.0  
+                va_distribution[:, 3] .= 0.0   # Z velocity = 0.0
+                
+                # This should not throw an error
+                @test_nowarn VortexStepMethod.frozen_wake!(body_aero, va_distribution)
+                
+                # Test that the function accepts the right number of velocity vectors
+                @test size(va_distribution, 1) == length(body_aero.panels)
+                @test size(va_distribution, 2) == 3  # 3D velocity vectors
+                
+            finally
+                # Clean up
+                rm(body_path; force=true)
+                rm(foil_path; force=true)
+            end
+        else
+            @test_skip "Ram air kite test data files not found, skipping frozen_wake! test"
+        end
+    end
+end
diff --git a/test/test_wing_geometry.jl b/test/wing_geometry/test_wing_geometry.jl
similarity index 100%
rename from test/test_wing_geometry.jl
rename to test/wing_geometry/test_wing_geometry.jl
diff --git a/test/yaml_geometry/alternate_airfoil.csv b/test/yaml_geometry/alternate_airfoil.csv
new file mode 100644
index 00000000..84b09166
--- /dev/null
+++ b/test/yaml_geometry/alternate_airfoil.csv
@@ -0,0 +1,7 @@
+alpha,cl,cd,cm
+-10.0,0.15,0.025,-0.015
+-5.0,0.55,0.018,-0.008
+0.0,1.1,0.012,0.001
+5.0,1.6,0.018,0.008
+10.0,1.9,0.03,0.012
+15.0,1.7,0.055,0.018
diff --git a/test/yaml_geometry/complex_wing.yaml b/test/yaml_geometry/complex_wing.yaml
new file mode 100644
index 00000000..ff38435d
--- /dev/null
+++ b/test/yaml_geometry/complex_wing.yaml
@@ -0,0 +1,18 @@
+wing_sections:
+  headers: [airfoil_id, LE_x, LE_y, LE_z, TE_x, TE_y, TE_z]
+  data:
+    - [1, 0.0, 5.0, 0.0, 2.0, 5.0, 0.5]
+    - [2, 0.2, 3.0, 0.2, 1.8, 3.0, 0.3]
+    - [2, 0.4, 1.0, 0.4, 1.6, 1.0, 0.1]
+    - [1, 0.5, 0.0, 0.5, 1.5, 0.0, 0.0]
+    - [2, 0.4, -1.0, 0.4, 1.6, -1.0, 0.1]
+    - [2, 0.2, -3.0, 0.2, 1.8, -3.0, 0.3]
+    - [1, 0.0, -5.0, 0.0, 2.0, -5.0, 0.5]
+
+wing_airfoils:
+  alpha_range: [-10, 10, 1]
+  reynolds: 1000000
+  headers: [airfoil_id, type, info_dict]
+  data:
+    - [1, polars, {csv_file_path: "standard_airfoil.csv"}]
+    - [2, polars, {csv_file_path: "alternate_airfoil.csv"}]
diff --git a/test/yaml_geometry/simple_wing.yaml b/test/yaml_geometry/simple_wing.yaml
new file mode 100644
index 00000000..e6c62baa
--- /dev/null
+++ b/test/yaml_geometry/simple_wing.yaml
@@ -0,0 +1,12 @@
+wing_sections:
+  headers: [airfoil_id, LE_x, LE_y, LE_z, TE_x, TE_y, TE_z]
+  data:
+    - [1, 0.0, 1.0, 0.0, 1.0, 1.0, 0.0]
+    - [1, 0.0, -1.0, 0.0, 1.0, -1.0, 0.0]
+
+wing_airfoils:
+  alpha_range: [-10, 10, 1]
+  reynolds: 1000000
+  headers: [airfoil_id, type, info_dict]
+  data:
+    - [1, polars, {csv_file_path: "standard_airfoil.csv"}]
diff --git a/test/yaml_geometry/standard_airfoil.csv b/test/yaml_geometry/standard_airfoil.csv
new file mode 100644
index 00000000..b675b096
--- /dev/null
+++ b/test/yaml_geometry/standard_airfoil.csv
@@ -0,0 +1,7 @@
+alpha,cl,cd,cm
+-10.0,0.1,0.02,-0.01
+-5.0,0.5,0.015,-0.005
+0.0,1.0,0.01,0.0
+5.0,1.5,0.015,0.005
+10.0,1.8,0.025,0.01
+15.0,1.6,0.05,0.015
diff --git a/test/yaml_geometry/test_load_polar_data.jl b/test/yaml_geometry/test_load_polar_data.jl
new file mode 100644
index 00000000..ccb487e1
--- /dev/null
+++ b/test/yaml_geometry/test_load_polar_data.jl
@@ -0,0 +1,126 @@
+using VortexStepMethod
+using VortexStepMethod: load_polar_data
+using LinearAlgebra
+using Test
+using YAML
+using Logging
+
+@testset "load_polar_data Function Tests" begin
+    # Setup temporary files for testing
+    test_csv_path = joinpath(tempdir(), "test_polar.csv")
+    
+    # Clean up function
+    function cleanup_test_files()
+        isfile(test_csv_path) && rm(test_csv_path; force=true)
+    end
+    
+    @testset "Valid CSV File" begin
+        # Create a valid CSV file with polar data
+        csv_content = """alpha,cl,cd,cm
+              -10.0,0.1,0.02,-0.01
+              -5.0,0.5,0.015,-0.005
+              0.0,1.0,0.01,0.0
+              5.0,1.5,0.015,0.005
+              10.0,1.8,0.025,0.01
+              15.0,1.6,0.05,0.015"""
+        write(test_csv_path, csv_content)
+        
+        aero_data, aero_model = load_polar_data(test_csv_path)
+        
+        @test aero_model == POLAR_VECTORS
+        @test aero_data isa Tuple{Vector{Float64}, Vector{Float64}, Vector{Float64}, Vector{Float64}}
+        @test length(aero_data) == 4  # alpha, cl, cd, cm
+        @test length(aero_data[1]) == 6  # 6 data points
+        
+        # Test that alpha is converted to radians
+        @test aero_data[1] ≈ deg2rad.([-10.0, -5.0, 0.0, 5.0, 10.0, 15.0])
+        
+        # Test coefficient values
+        @test aero_data[2] ≈ [0.1, 0.5, 1.0, 1.5, 1.8, 1.6]  # cl
+        @test aero_data[3] ≈ [0.02, 0.015, 0.01, 0.015, 0.025, 0.05]  # cd
+        @test aero_data[4] ≈ [-0.01, -0.005, 0.0, 0.005, 0.01, 0.015]  # cm
+    end
+    
+    @testset "Different Column Order" begin
+        # Test with different column ordering
+        csv_content = """cm,alpha,cd,cl
+                -0.01,-10.0,0.02,0.1
+                -0.005,-5.0,0.015,0.5
+                0.0,0.0,0.01,1.0"""
+        write(test_csv_path, csv_content)
+        
+        aero_data, aero_model = load_polar_data(test_csv_path)
+        
+        @test aero_model == POLAR_VECTORS
+        @test aero_data[1] ≈ deg2rad.([-10.0, -5.0, 0.0])  # alpha
+        @test aero_data[2] ≈ [0.1, 0.5, 1.0]  # cl
+        @test aero_data[3] ≈ [0.02, 0.015, 0.01]  # cd
+        @test aero_data[4] ≈ [-0.01, -0.005, 0.0]  # cm
+    end
+    
+    @testset "Case Insensitive Headers" begin
+        # Test with mixed case headers
+        csv_content = """ALPHA,CL,CD,CM
+          0.0,1.0,0.01,0.0
+          5.0,1.5,0.015,0.005"""
+        write(test_csv_path, csv_content)
+        
+        aero_data, aero_model = load_polar_data(test_csv_path)
+        
+        @test aero_model == POLAR_VECTORS
+        @test length(aero_data[1]) == 2
+    end
+    
+    @testset "Missing File" begin
+        nonexistent_path = joinpath(tempdir(), "nonexistent.csv")
+        aero_data, aero_model = suppress_warnings(() -> load_polar_data(nonexistent_path))
+        
+        @test aero_model == INVISCID
+        @test aero_data === nothing
+    end
+    
+    @testset "Empty File Path" begin
+        aero_data, aero_model = suppress_warnings(() -> load_polar_data(""))
+        
+        @test aero_model == INVISCID
+        @test aero_data === nothing
+    end
+    
+    @testset "Invalid CSV Format" begin
+        # Missing required columns
+        csv_content = """alpha,cl
+        0.0,1.0
+        5.0,1.5"""
+        write(test_csv_path, csv_content)
+        
+        aero_data, aero_model = suppress_warnings(() -> load_polar_data(test_csv_path))
+        
+        @test aero_model == INVISCID
+        @test aero_data === nothing
+    end
+    
+    @testset "Empty CSV File" begin
+        write(test_csv_path, "")
+        
+        aero_data, aero_model = suppress_warnings(() -> load_polar_data(test_csv_path))
+        
+        @test aero_model == INVISCID
+        @test aero_data === nothing
+    end
+    
+    @testset "Malformed Data" begin
+        # Invalid numeric data
+        csv_content = """alpha,cl,cd,cm
+        invalid,1.0,0.01,0.0
+        5.0,1.5,0.015,0.005"""
+        write(test_csv_path, csv_content)
+        
+        aero_data, aero_model = suppress_warnings(() -> load_polar_data(test_csv_path))
+        
+        @test aero_model == INVISCID
+        @test aero_data === nothing
+    end
+    
+    # Cleanup after all tests
+    cleanup_test_files()
+end
diff --git a/test/yaml_geometry/test_wing_constructor.jl b/test/yaml_geometry/test_wing_constructor.jl
new file mode 100644
index 00000000..b7b30a45
--- /dev/null
+++ b/test/yaml_geometry/test_wing_constructor.jl
@@ -0,0 +1,267 @@
+using VortexStepMethod
+using VortexStepMethod: load_polar_data
+using LinearAlgebra
+using Test
+using YAML
+using Logging
+
+@testset "Wing Constructor Tests" begin
+    # Setup temporary files for testing
+    test_yaml_path = joinpath(tempdir(), "test_wing.yaml")
+    test_polar_dir = joinpath(tempdir(), "polars")
+    
+    # Clean up function
+    function cleanup_test_files()
+        test_dir = dirname(test_yaml_path)
+        for file in [test_yaml_path, 
+                     joinpath(test_dir, "standard_airfoil.csv"),
+                     joinpath(test_dir, "alternate_airfoil.csv")]
+            isfile(file) && rm(file; force=true)
+        end
+        isdir(test_polar_dir) && rm(test_polar_dir; recursive=true, force=true)
+    end
+    
+    # Create polar data directory and files
+    mkpath(test_polar_dir)
+    
+    # Copy the actual polar files to the temp directory for tests that reference them
+    cp(test_data_path("yaml_geometry", "standard_airfoil.csv"), joinpath(test_polar_dir, "1.csv"); force=true)
+    cp(test_data_path("yaml_geometry", "alternate_airfoil.csv"), joinpath(test_polar_dir, "2.csv"); force=true)
+    
+    # Also copy them to the test directory itself for direct reference tests
+    test_dir = dirname(test_yaml_path)
+    cp(test_data_path("yaml_geometry", "standard_airfoil.csv"), joinpath(test_dir, "standard_airfoil.csv"); force=true)
+    cp(test_data_path("yaml_geometry", "alternate_airfoil.csv"), joinpath(test_dir, "alternate_airfoil.csv"); force=true)
+    
+    @testset "Valid YAML Wing Construction" begin
+        # Use the actual YAML file from the test data
+        cp(test_data_path("yaml_geometry", "simple_wing.yaml"), test_yaml_path; force=true)
+        
+        wing = Wing(test_yaml_path; n_panels=4, n_groups=2)
+        
+        @test wing isa Wing
+        @test wing.n_panels == 4
+        @test wing.n_groups == 2
+        @test wing.spanwise_distribution == LINEAR
+        @test wing.spanwise_direction ≈ [0.0, 1.0, 0.0]
+        @test length(wing.sections) == 2  # simple_wing has 2 sections
+        
+        # Test section coordinates (sections are sorted by spanwise position)
+        # simple_wing.yaml has: [1, 0.0, 1.0, 0.0, 1.0, 1.0, 0.0] and [1, 0.0, -1.0, 0.0, 1.0, -1.0, 0.0]
+        # Sorted by y-coordinate: y=1.0, y=-1.0
+        @test wing.sections[1].LE_point ≈ [0.0, 1.0, 0.0]
+        @test wing.sections[1].TE_point ≈ [1.0, 1.0, 0.0]
+        @test wing.sections[2].LE_point ≈ [0.0, -1.0, 0.0]
+        @test wing.sections[2].TE_point ≈ [1.0, -1.0, 0.0]
+        
+        # Test that sections have polar data
+        @test wing.sections[1].aero_model == POLAR_VECTORS
+        @test wing.sections[2].aero_model == POLAR_VECTORS
+        
+        # Test polar data is loaded
+        @test wing.sections[1].aero_data isa Tuple
+        @test length(wing.sections[1].aero_data) == 4
+        @test length(wing.sections[1].aero_data[1]) >= 3  # at least 3 alpha points
+    end
+    
+    @testset "Wing Constructor Parameters" begin
+        # Use the simple_wing.yaml and test custom parameters
+        cp(test_data_path("yaml_geometry", "simple_wing.yaml"), test_yaml_path; force=true)
+        
+        # Test custom parameters
+        wing = Wing(
+            test_yaml_path;
+            n_panels=8,
+            n_groups=4,
+            spanwise_distribution=COSINE,
+            remove_nan=false
+        )
+        
+        @test wing.n_panels == 8
+        @test wing.n_groups == 4
+        @test wing.spanwise_distribution == COSINE
+        @test !wing.remove_nan
+    end
+    
+    @testset "Missing Polar Files" begin
+        # Create YAML with non-existent polar files
+        yaml_content = """
+wing_sections:
+  headers: [airfoil_id, LE_x, LE_y, LE_z, TE_x, TE_y, TE_z]
+  data:
+    - [1, 0.0, 1.0, 0.0, 1.0, 1.0, 0.0]
+    - [1, 0.0, -1.0, 0.0, 1.0, -1.0, 0.0]
+
+wing_airfoils:
+  alpha_range: [-10, 10, 1]
+  reynolds: 1000000
+  headers: [airfoil_id, type, info_dict]
+  data:
+    - [1, polars, {csv_file_path: "nonexistent.csv"}]
+"""
+        write(test_yaml_path, yaml_content)
+        
+        wing = suppress_warnings(() -> Wing(test_yaml_path; n_panels=2))
+        
+        # Should fall back to INVISCID model
+        @test wing.sections[1].aero_model == INVISCID
+        @test wing.sections[1].aero_data === nothing
+    end
+    
+    @testset "Sections Without Polar Files" begin
+        # Create YAML with empty polar file paths
+        yaml_content = """
+wing_sections:
+  headers: [airfoil_id, LE_x, LE_y, LE_z, TE_x, TE_y, TE_z]
+  data:
+    - [1, 0.0, 1.0, 0.0, 1.0, 1.0, 0.0]
+    - [1, 0.0, -1.0, 0.0, 1.0, -1.0, 0.0]
+
+wing_airfoils:
+  alpha_range: [-10, 10, 1]
+  reynolds: 1000000
+  headers: [airfoil_id, type, info_dict]
+  data:
+    - [1, polars, {csv_file_path: ""}]
+"""
+        write(test_yaml_path, yaml_content)
+        
+        wing = suppress_warnings(() -> Wing(test_yaml_path; n_panels=2))
+        
+        # Should fall back to INVISCID model
+        @test wing.sections[1].aero_model == INVISCID
+    end
+    
+    @testset "Invalid Parameters" begin
+        yaml_content = """
+wing_sections:
+  headers: [airfoil_id, LE_x, LE_y, LE_z, TE_x, TE_y, TE_z]
+  data:
+    - [1, 0.0, 1.0, 0.0, 1.0, 1.0, 0.0]
+    - [1, 0.0, -1.0, 0.0, 1.0, -1.0, 0.0]
+
+wing_airfoils:
+  alpha_range: [-10, 10, 1]
+  reynolds: 1000000
+  headers: [airfoil_id, type, info_dict]
+  data:
+    - [1, polars, {csv_file_path: "polars/1.csv"}]
+"""
+        write(test_yaml_path, yaml_content)
+        
+        # Test invalid n_panels/n_groups combination
+        @test_throws ArgumentError Wing(test_yaml_path; n_panels=5, n_groups=2)
+        
+        # Test invalid spanwise direction
+        @test_throws ArgumentError Wing(test_yaml_path; spanwise_direction=[1.0, 0.0, 0.0])
+    end
+    
+    @testset "Relative Path Resolution" begin
+        # Test that relative paths in CSV files are resolved relative to YAML file
+        subdir = joinpath(tempdir(), "subtest")
+        mkpath(subdir)
+        
+        # Copy the simple wing file to subdirectory
+        subdir_yaml_path = joinpath(subdir, "wing.yaml")
+        cp(test_data_path("yaml_geometry", "simple_wing.yaml"), subdir_yaml_path; force=true)
+        
+        # Copy the polar file to subdirectory too
+        subdir_polar_path = joinpath(subdir, "standard_airfoil.csv")
+        cp(test_data_path("yaml_geometry", "standard_airfoil.csv"), subdir_polar_path; force=true)
+        
+        wing = Wing(subdir_yaml_path; n_panels=2)
+        
+        # Should successfully load polar data with relative path
+        @test wing.sections[1].aero_model == POLAR_VECTORS
+        @test wing.sections[1].aero_data isa Tuple
+        @test wing.sections[2].aero_model == POLAR_VECTORS
+        @test wing.sections[2].aero_data isa Tuple
+        
+        # Cleanup
+        rm(subdir; recursive=true)
+    end
+    
+    @testset "Complex Wing Geometry" begin
+        # Use the actual complex_wing.yaml file
+        cp(test_data_path("yaml_geometry", "complex_wing.yaml"), test_yaml_path; force=true)
+        
+        wing = Wing(test_yaml_path; n_panels=12, n_groups=3)
+        
+        @test wing.n_panels == 12
+        @test wing.n_groups == 3
+        @test length(wing.sections) == 7
+        
+        # Test that different airfoil_ids get different polar data
+        @test wing.sections[1].aero_model == POLAR_VECTORS
+        @test wing.sections[2].aero_model == POLAR_VECTORS
+        
+        # Verify geometric progression along wingspan
+        @test wing.sections[1].LE_point[2] == 5.0   # First section at y=5
+        @test wing.sections[4].LE_point[2] == 0.0   # Middle section at y=0
+        @test wing.sections[7].LE_point[2] == -5.0  # Last section at y=-5
+    end
+    
+    @testset "VSMSettings Constructor" begin
+        # Test Wing constructor that takes VSMSettings
+        # Use the actual simple_wing.yaml file
+        simple_wing_file = test_data_path("yaml_geometry", "simple_wing.yaml")
+        
+        # Create VSMSettings with wing configuration
+        settings = VSMSettings()
+        settings.wings = [WingSettings(
+            geometry_file=simple_wing_file,
+            n_panels=6,
+            n_groups=3,
+            spanwise_panel_distribution=COSINE
+        )]
+        
+        # Test Wing constructor with VSMSettings
+        wing = Wing(settings)
+        
+        @test wing isa Wing
+        @test wing.n_panels == 6
+        @test wing.n_groups == 3
+        @test wing.spanwise_distribution == COSINE
+        @test length(wing.sections) == 2
+        @test wing.sections[1].aero_model == POLAR_VECTORS
+        @test wing.sections[2].aero_model == POLAR_VECTORS
+    end
+    
+    @testset "Shared Test Data Usage" begin
+        # Demonstrate using module-specific test data files
+        simple_wing_file = test_data_path("yaml_geometry", "simple_wing.yaml")
+        @test isfile(simple_wing_file)
+        
+        # Test basic Wing construction with shared data
+        wing = Wing(simple_wing_file; n_panels=4, n_groups=2)
+        @test wing isa Wing
+        @test wing.n_panels == 4
+        @test wing.n_groups == 2
+        @test length(wing.sections) == 2
+        
+        # Test complex wing construction
+        complex_wing_file = test_data_path("yaml_geometry", "complex_wing.yaml")
+        @test isfile(complex_wing_file)
+        
+        complex_wing = Wing(complex_wing_file; n_panels=12, n_groups=3)
+        @test complex_wing isa Wing
+        @test complex_wing.n_panels == 12
+        @test complex_wing.n_groups == 3
+        @test length(complex_wing.sections) == 7
+        
+        # Verify polar data is loaded from shared files
+        @test complex_wing.sections[1].aero_model == POLAR_VECTORS
+        @test complex_wing.sections[1].aero_data isa Tuple
+        
+        # Test with module-specific convenience function - create a standard wing for this test
+        standard_wing_file = simple_wing_file  # Use simple_wing as our "standard"
+        @test isfile(standard_wing_file)
+        
+        standard_wing = Wing(standard_wing_file; n_panels=2, n_groups=1)
+        @test standard_wing isa Wing
+        @test length(standard_wing.sections) == 2
+    end
+    
+    # Cleanup after all tests
+    cleanup_test_files()
+end
diff --git a/test/yaml_geometry/test_yaml_geometry.jl b/test/yaml_geometry/test_yaml_geometry.jl
new file mode 100644
index 00000000..12daa54f
--- /dev/null
+++ b/test/yaml_geometry/test_yaml_geometry.jl
@@ -0,0 +1,7 @@
+using Test
+
+@testset "YAML Geometry Tests" begin
+    # Include specific test files for better organization
+    include("test_load_polar_data.jl")
+    include("test_wing_constructor.jl")
+end