OpenSourceAWE · 1-Bart-1 · Jul 18, 2026 · Jul 18, 2026 · Jul 19, 2026 · Jul 19, 2026
diff --git a/codecov.yml b/codecov.yml
@@ -0,0 +1,9 @@
+coverage:
+  status:
+    project:
+      default:
+        target: auto
+        threshold: 0%
+    patch:
+      default:
+        target: 70%
diff --git a/docs/src/functions.md b/docs/src/functions.md
@@ -9,16 +9,13 @@ calculate_span
 calculate_projected_area
 ```
 
-## Surface-pressure (Cp) tables
-The Cp table types and IO live in the core package; the generation of Cp tables
-(from XFoil/NeuralFoil) lives in `AirfoilAero`.
+## Surface aero (contour + Cp + cf) tables
+The per-section surface aero table type and its loader live in the core package; the
+generation and CSV/dat writing (from XFoil/NeuralFoil) live in `AirfoilAero`.
 ```@docs
-CpData
-CpPolar
-read_cp_data
-write_cp_data
-cp_distribution
-delta_cp
+SectionAero
+section_surface
+read_section_aero
 ```
 
 ## Airfoil aerodynamics (AirfoilAero)
@@ -47,7 +44,10 @@ neuralfoil_aero
 generate_aero_matrices
 generate_polar_from_coordinates
 generate_polar_from_dat
-generate_cp_polar
+generate_airfoil_aero
+generate_section_aero
+generate_airfoils
+write_section_aero
 ```
 
 ## OBJ mesh conversion (ObjAdapter)
@@ -59,12 +59,22 @@ CurrentModule = VortexStepMethod.ObjAdapter
 ```
 ```@docs
 obj_to_yaml
-generate_section_polars
 write_yaml
 perpendicular_sections
 plot_airfoils
 plot_slices_3d
 ```
+
+## Surfplan conversion (SurfplanAdapter)
+These live in the `SurfplanAdapter` submodule of `VortexStepMethod`, which converts the
+output of the (Python) SurfplanAdapter export into the native, VSM-loadable YAML/CSV
+geometry format. Load it with `using VortexStepMethod.SurfplanAdapter`.
+```@meta
+CurrentModule = VortexStepMethod.SurfplanAdapter
+```
+```@docs
+surfplan_to_aero_yaml
+```
 ```@meta
 CurrentModule = VortexStepMethod
 ```

diff --git a/docs/src/private_functions.md b/docs/src/private_functions.md
@@ -44,6 +44,7 @@ update_panel_properties!
 build_interps
 panel_interp_types
 reinit!(wing::AbstractWing)
+reinit!(panel::Panel, section_1::Section, section_2::Section, aero_center, control_point, bound_point_1, bound_point_2, x_airf, y_airf, z_airf, delta, vec, spanwise_direction)
 rotated_te
 calculate_filaments_for_plotting
 ```
@@ -54,6 +55,7 @@ unrefined_deform!
 deform!
 compute_refined_panel_mapping!
 compute_refined_section_interpolation!
+copy_sections
 copy_sections_to_refined!
 _apply_refined_section_thetas!
 _panel_thetas_to_section_thetas!
@@ -74,15 +76,15 @@ calculate_new_aero_data
 assemble_polar_matrix
 load_matrix_polar_data
 read_aero_matrix
-write_aero_matrix
+read_dat
+read_node_table
 interpolate_matrix_nans!
 remove_vector_nans
 generate_polar_data
 extract_literature_polar_data
 parse_literature_column
-interpolate_cp_to_refined!
-prepare_cp_output!
-validate_cp_sections
+interpolate_section_aero_to_refined!
+validate_section_aero
 ```
 
 ### Examples
@@ -115,9 +117,7 @@ flood_outside
 trace_level_set
 largest_linking_gap
 resample_arc
-resample_x
 smooth_turning!
-split_surfaces
 ```
 
 ### NeuralFoil network
@@ -143,7 +143,11 @@ read_dat_coordinates
 write_dat
 write_polar_csv
 write_polar_matrix_csv
-fill_slice_nans!
+write_aero_matrix
+write_node_table
+flat_plate_cf
+neuralfoil_contour_solution
+fill_node_nans!
 ```
 
 ## OBJ mesh conversion (ObjAdapter)
@@ -183,6 +187,7 @@ set_axes_equal_makie!
 map_airfoil_3d
 fitted_airfoil_3d
 generated_slices
+airfoil_skin_geometry
 Makie.plot!(ax, panel::VortexStepMethod.Panel)
 Makie.plot!(ax, body::VortexStepMethod.BodyAerodynamics)
 Makie.plot!(body::VortexStepMethod.BodyAerodynamics)

diff --git a/examples/V3_neuralfoil.jl b/examples/V3_neuralfoil.jl
@@ -59,13 +59,14 @@ fig_slices_3d = plot_slices_3d(OBJ_PATH; n_slices=N_SLICES, rotation=ROTATION,
                                n_bins=N_BINS, wrap_method=WRAP)
 GLMakie.save("V3_slices_3d.png", fig_slices_3d)
 
-# Generate per-slice NeuralFoil polars from the shrink-wrapped sections. XFoil is also
-# supported (pass `solver=XFoilSolver(...)`) but its panel method does not converge on
-# the V3's thin, tube-nosed membrane airfoils, so NeuralFoil is used here.
-println("Generating NeuralFoil polars from OBJ mesh...")
-generate_section_polars(OBJ_PATH, POLARS_DIR; n_slices=N_SLICES, Re=RE,
-    rotation=ROTATION, n_bins=N_BINS, wrap_method=WRAP,
-    solver=NF_SOLVER, delta_range=DELTA_RANGE, verbose=true)
+# `obj_to_yaml` generates the whole aero geometry from the OBJ: shape (.dat), polar CSV,
+# and Cp/cf tables plus a geometry.yaml. XFoil (`aero_solver=XFoilSolver(...)`) also works
+# but doesn't converge on the V3's concave slices (the sharp corner behind the leading
+# edge), so NeuralFoil is used here.
+println("Generating V3 aero geometry from OBJ (obj_to_yaml)...")
+gen_dir = joinpath("data", "TUDELFT_V3_KITE", "generated_neuralfoil")
+nf_yaml = obj_to_yaml(OBJ_PATH, gen_dir; n_sections=N_SLICES, Re=RE,
+    rotation=ROTATION, wrap_method=WRAP, aero_solver=NF_SOLVER, verbose=true)
 
 # Flight conditions
 v_a = 10.0
@@ -82,29 +83,12 @@ body_cfd = BodyAerodynamics([wing_cfd])
 VortexStepMethod.reinit!(body_cfd)
 solver_cfd = Solver(body_cfd, settings_cfd)
 
-# Build a wing whose every airfoil points at a generated POLAR_VECTORS CSV under
-# `polars_subdir`. Repoints a copy of the awesIO geometry and loads it as a normal
-# uniform POLAR_VECTORS wing — no manual section surgery needed.
-using YAML
-yaml_path = joinpath("data", "TUDELFT_V3_KITE", "aero_geometry.yaml")
-function build_polar_wing(polars_subdir, out_name)
-    geom = YAML.load_file(yaml_path)
-    for (i, airfoil) in enumerate(geom["wing_airfoils"]["data"])
-        airfoil[2] = "polars"
-        airfoil[3] = Dict("csv_file_path" => "$polars_subdir/$i.csv")
-    end
-    out_yaml = joinpath("data", "TUDELFT_V3_KITE", out_name)
-    write_yaml(out_yaml, geom)
-    wing = Wing(out_yaml; n_panels=50, spanwise_distribution=LINEAR)
-    refine!(wing)
-    body = BodyAerodynamics([wing])
-    VortexStepMethod.reinit!(body)
-    s = Solver(body, settings_cfd)
-    return s, body
-end
-
 println("Creating wing with NeuralFoil polars...")
-solver_nf, body_nf = build_polar_wing("polars_neuralfoil", "aero_geometry_neuralfoil.yaml")
+wing_nf = Wing(nf_yaml; n_panels=50, spanwise_distribution=LINEAR)
+refine!(wing_nf)
+body_nf = BodyAerodynamics([wing_nf])
+VortexStepMethod.reinit!(body_nf)
+solver_nf = Solver(body_nf, settings_cfd)
 
 # Compare CFD-polar and NeuralFoil-polar wings against published references
 # (Poland 2025 RANS CFD and wind tunnel). `plot_polars` sweeps each solver over the