From 7b5a0711d2a3fe62e11a8b66464045146d26214f Mon Sep 17 00:00:00 2001 From: Bart Date: Wed, 18 Mar 2026 16:51:58 +0100 Subject: [PATCH 1/4] Add billowing mode and example --- .../aero_geometry_coarse_discretisation.yaml | 171 ++++++++++++++++++ .../polars_CFD_NF_combined/1.csv | 132 ++++++++++++++ .../polars_CFD_NF_combined/10.csv | 132 ++++++++++++++ .../polars_CFD_NF_combined/11.csv | 132 ++++++++++++++ .../polars_CFD_NF_combined/12.csv | 132 ++++++++++++++ .../polars_CFD_NF_combined/13.csv | 132 ++++++++++++++ .../polars_CFD_NF_combined/14.csv | 132 ++++++++++++++ .../polars_CFD_NF_combined/15.csv | 132 ++++++++++++++ .../polars_CFD_NF_combined/16.csv | 132 ++++++++++++++ .../polars_CFD_NF_combined/17.csv | 132 ++++++++++++++ .../polars_CFD_NF_combined/18.csv | 132 ++++++++++++++ .../polars_CFD_NF_combined/19.csv | 132 ++++++++++++++ .../polars_CFD_NF_combined/2.csv | 132 ++++++++++++++ .../polars_CFD_NF_combined/3.csv | 132 ++++++++++++++ .../polars_CFD_NF_combined/4.csv | 132 ++++++++++++++ .../polars_CFD_NF_combined/5.csv | 132 ++++++++++++++ .../polars_CFD_NF_combined/6.csv | 132 ++++++++++++++ .../polars_CFD_NF_combined/7.csv | 132 ++++++++++++++ .../polars_CFD_NF_combined/8.csv | 132 ++++++++++++++ .../polars_CFD_NF_combined/9.csv | 132 ++++++++++++++ data/TUDELFT_V3_KITE/vsm_settings_coarse.yaml | 84 +++++++++ examples/billowing.jl | 147 +++++++++++++++ src/VortexStepMethod.jl | 8 +- src/body_aerodynamics.jl | 5 +- src/obj_geometry.jl | 2 +- src/settings.jl | 4 + src/wing_geometry.jl | 170 ++++++++++++++++- src/yaml_geometry.jl | 8 +- 28 files changed, 3095 insertions(+), 12 deletions(-) create mode 100644 data/TUDELFT_V3_KITE/aero_geometry_coarse_discretisation.yaml create mode 100644 data/TUDELFT_V3_KITE/polars_CFD_NF_combined/1.csv create mode 100644 data/TUDELFT_V3_KITE/polars_CFD_NF_combined/10.csv create mode 100644 data/TUDELFT_V3_KITE/polars_CFD_NF_combined/11.csv create mode 100644 data/TUDELFT_V3_KITE/polars_CFD_NF_combined/12.csv create mode 100644 data/TUDELFT_V3_KITE/polars_CFD_NF_combined/13.csv create mode 100644 data/TUDELFT_V3_KITE/polars_CFD_NF_combined/14.csv create mode 100644 data/TUDELFT_V3_KITE/polars_CFD_NF_combined/15.csv create mode 100644 data/TUDELFT_V3_KITE/polars_CFD_NF_combined/16.csv create mode 100644 data/TUDELFT_V3_KITE/polars_CFD_NF_combined/17.csv create mode 100644 data/TUDELFT_V3_KITE/polars_CFD_NF_combined/18.csv create mode 100644 data/TUDELFT_V3_KITE/polars_CFD_NF_combined/19.csv create mode 100644 data/TUDELFT_V3_KITE/polars_CFD_NF_combined/2.csv create mode 100644 data/TUDELFT_V3_KITE/polars_CFD_NF_combined/3.csv create mode 100644 data/TUDELFT_V3_KITE/polars_CFD_NF_combined/4.csv create mode 100644 data/TUDELFT_V3_KITE/polars_CFD_NF_combined/5.csv create mode 100644 data/TUDELFT_V3_KITE/polars_CFD_NF_combined/6.csv create mode 100644 data/TUDELFT_V3_KITE/polars_CFD_NF_combined/7.csv create mode 100644 data/TUDELFT_V3_KITE/polars_CFD_NF_combined/8.csv create mode 100644 data/TUDELFT_V3_KITE/polars_CFD_NF_combined/9.csv create mode 100644 data/TUDELFT_V3_KITE/vsm_settings_coarse.yaml create mode 100644 examples/billowing.jl diff --git a/data/TUDELFT_V3_KITE/aero_geometry_coarse_discretisation.yaml b/data/TUDELFT_V3_KITE/aero_geometry_coarse_discretisation.yaml new file mode 100644 index 00000000..4b5fc74d --- /dev/null +++ b/data/TUDELFT_V3_KITE/aero_geometry_coarse_discretisation.yaml @@ -0,0 +1,171 @@ +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 + # --------------------------------------------------------------- + # NOTE: Reduced to 10 sections to match 20 structural WING points (10 LE/TE pairs) + # Constraint: n_structural_points (20) == 2 * n_vsm_sections (10) + # Selected sections match structural point spanwise positions + headers: [airfoil_id, LE_x, LE_y, LE_z, TE_x, TE_y, TE_z] + data: + # Sections match structural points exactly from struc_geometry.yaml + # Section 1: points 2 (LE) and 3 (TE) + - [ + 18, + -0.16686417, + 4.07190711, + 8.25938552, + 0.8950856, + 4.23504033, + 8.28564737, + ] + # Section 2: points 4 (LE) and 5 (TE) + - [ + 15, + -0.66385373, + 3.97158462, + 9.10345727, + 0.84466799, + 4.04893109, + 9.16869541, + ] + # Section 3: points 6 (LE) and 7 (TE) + - [ + 11, + -1.00179344, + 3.13938093, + 10.08117033, + 0.95411064, + 3.19044693, + 10.20618443, + ] + # Section 4: points 8 (LE) and 9 (TE) + - [ + 7, + -1.11933902, + 1.96778538, + 10.69146438, + 1.03150699, + 1.98490264, + 10.81013669, + ] + # Section 5: points 10 (LE) and 11 (TE) + - [ + 3, + -1.16537227, + 0.67379745, + 10.96630823, + 1.09790203, + 0.6605361, + 11.06585663, + ] + # Section 6: points 12 (LE) and 13 (TE) - mirror of section 5 + - [ + 3, + -1.16537227, + -0.67379745, + 10.96630823, + 1.09790203, + -0.6605361, + 11.06585663, + ] + # Section 7: points 14 (LE) and 15 (TE) - mirror of section 4 + - [ + 7, + -1.11933902, + -1.96778538, + 10.69146438, + 1.03150699, + -1.98490264, + 10.81013669, + ] + # Section 8: points 16 (LE) and 17 (TE) - mirror of section 3 + - [ + 11, + -1.00179344, + -3.13938093, + 10.08117033, + 0.95411064, + -3.19044693, + 10.20618443, + ] + # Section 9: points 18 (LE) and 19 (TE) - mirror of section 2 + - [ + 15, + -0.66385373, + -3.97158462, + 9.10345727, + 0.84466799, + -4.04893109, + 9.16869541, + ] + # Section 10: points 20 (LE) and 21 (TE) - mirror of section 1 + - [ + 18, + -0.16686417, + -4.07190711, + 8.25938552, + 0.8950856, + -4.23504033, + 8.28564737, + ] + +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: [-15, 50, 0.5] # [deg], in this range the polars are calculated + reynolds: !!float 1e6 # Reynolds number + headers: [airfoil_id, type, info_dict] + data: + - [1, polars, { csv_file_path: '2D_polars_drag_adjusted/1.csv' }] + - [2, polars, { csv_file_path: '2D_polars_drag_adjusted/2.csv' }] + - [3, polars, { csv_file_path: '2D_polars_drag_adjusted/3.csv' }] + - [4, polars, { csv_file_path: '2D_polars_drag_adjusted/4.csv' }] + - [5, polars, { csv_file_path: '2D_polars_drag_adjusted/5.csv' }] + - [6, polars, { csv_file_path: '2D_polars_drag_adjusted/6.csv' }] + - [7, polars, { csv_file_path: '2D_polars_drag_adjusted/7.csv' }] + - [8, polars, { csv_file_path: '2D_polars_drag_adjusted/8.csv' }] + - [9, polars, { csv_file_path: '2D_polars_drag_adjusted/9.csv' }] + - [10, polars, { csv_file_path: '2D_polars_drag_adjusted/10.csv' }] + - [11, polars, { csv_file_path: '2D_polars_drag_adjusted/11.csv' }] + - [12, polars, { csv_file_path: '2D_polars_drag_adjusted/12.csv' }] + - [13, polars, { csv_file_path: '2D_polars_drag_adjusted/13.csv' }] + - [14, polars, { csv_file_path: '2D_polars_drag_adjusted/14.csv' }] + - [15, polars, { csv_file_path: '2D_polars_drag_adjusted/15.csv' }] + - [16, polars, { csv_file_path: '2D_polars_drag_adjusted/16.csv' }] + - [17, polars, { csv_file_path: '2D_polars_drag_adjusted/17.csv' }] + - [18, polars, { csv_file_path: '2D_polars_drag_adjusted/18.csv' }] + - [19, polars, { csv_file_path: '2D_polars_drag_adjusted/19.csv' }] diff --git a/data/TUDELFT_V3_KITE/polars_CFD_NF_combined/1.csv b/data/TUDELFT_V3_KITE/polars_CFD_NF_combined/1.csv new file mode 100644 index 00000000..379e8c2c --- /dev/null +++ b/data/TUDELFT_V3_KITE/polars_CFD_NF_combined/1.csv @@ -0,0 +1,132 @@ +alpha,Cl,Cd,Cm +-14.999999999999998,-0.7815989424727691,0.26690486928639234,0.1513115712127311 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+-7.499999999999999,-0.4811686704299466,0.11717547097844778,0.15131157121273106 +-7.0,-0.4324606994688453,0.10760532853756,0.1367939817737111 +-6.5,-0.3853819090913009,0.0988588209892892,0.1228446364449695 +-6.000000000000001,-0.33992582965760837,0.09097570035474242,0.10946484035339861 +-5.5,-0.2960859915280623,0.0839957186550263,0.096655898625891 +-5.0,-0.2538559250629577,0.0779586279112478,0.0844191163893389 +-4.5,-0.2159550434674728,0.0727676807943206,0.0730550516548853 +-4.0,-0.1829588587323138,0.0682091846241277,0.0626174354043963 +-3.5,-0.1516450493960662,0.0641474733952293,0.0527373322208485 +-3.0000000000000004,-0.11879129399731583,0.06044688110218561,0.04304580668721851 +-2.5,-0.0811752710746482,0.0569717417395568,0.0331739233864828 +-2.0,-0.0355746591666493,0.0535863893019032,0.0227527469016182 +-1.5000000000000002,0.02622609975082757,0.0503504235725568,0.011481449300827406 +-1.0,0.1042908628198079,0.0473577829911575,-0.0002656553047875 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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/v3/aero_geometry.yaml + n_panels: 54 # Total number of panels along wingspan + spanwise_panel_distribution: SPLIT_PROVIDED # 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 + use_prior_polar: true # Use previously computed polars if available + +# 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 + #correct_aoa: false # Defaults to false, meaning the computed AoA at 3/4c is used + + # --- 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 + use_gamma_prev: false # avoid delayed stall predictions + + # --- Output Control --- + calc_only_f_and_gamma: false # true=compute only forces & circulation + + correct_aoa: false diff --git a/examples/billowing.jl b/examples/billowing.jl new file mode 100644 index 00000000..34c9f4e2 --- /dev/null +++ b/examples/billowing.jl @@ -0,0 +1,147 @@ +using LinearAlgebra +using VortexStepMethod +using GLMakie +using DelimitedFiles + +PLOT = true +USE_TEX = false +BILLOWING_ANGLE = billowing_angle_from_percentage(5) # Half-angle of billowing arc [rad] + +# Data paths (all within this repo) +project_dir = dirname(dirname(pathof(VortexStepMethod))) +v3_dir = joinpath(project_dir, "data", "TUDELFT_V3_KITE") +polar_dir = joinpath(v3_dir, "polars_CFD_NF_combined") + +# Literature results +lit_dir = joinpath(v3_dir, "literature_results") +literature_paths = [ + joinpath(lit_dir, "CFD_RANS_Rey_5e5_Poland2025_alpha_sweep_beta_0_NoStruts.csv"), + joinpath(lit_dir, "CFD_RANS_Rey_10e5_Poland2025_alpha_sweep_beta_0.csv"), + joinpath(lit_dir, "python_alpha_sweep.csv"), + joinpath(lit_dir, "windtunnel_alpha_sweep_beta_00_0_Poland_2025_Rey_5e5.csv"), +] +labels = [ + "VSM flat", + "VSM billowing $(round(Int, rad2deg(BILLOWING_ANGLE)))°", + "CFD Re=5e5", + "CFD Re=10e5", + "VSM Python Re=5e5", + "WindTunnel Re=5e5", +] + +# Load solver settings (coarse: 36 panels, matches 10-section geometry) +settings_data = VortexStepMethod.YAML.load_file( + joinpath(v3_dir, "vsm_settings_coarse.yaml")) +condition_cfg = settings_data["condition"] +solver_cfg = settings_data["solver_settings"] +n_panels = settings_data["wings"][1]["n_panels"] + +# Load coarse geometry (10 structural rib sections) +geom_data = VortexStepMethod.YAML.load_file( + joinpath(v3_dir, "aero_geometry_coarse_discretisation.yaml")) +section_headers = geom_data["wing_sections"]["headers"] +section_rows = geom_data["wing_sections"]["data"] + +function build_wing(; distribution=SPLIT_PROVIDED, billowing_angle=0.0) + wing = Wing(n_panels; + spanwise_distribution=distribution, + billowing_angle=billowing_angle) + for row in section_rows + d = Dict(zip(section_headers, row)) + le = [d["LE_x"], d["LE_y"], d["LE_z"]] + te = [d["TE_x"], d["TE_y"], d["TE_z"]] + csv_path = joinpath(polar_dir, "$(d["airfoil_id"]).csv") + aero_data, aero_model = load_polar_data(csv_path) + add_section!(wing, le, te, aero_model, aero_data) + end + refine!(wing) + return wing +end + +# --- Wing without billowing --- +wing_flat = build_wing() +body_aero_flat = BodyAerodynamics([wing_flat]) +VortexStepMethod.reinit!(body_aero_flat) + +# --- Wing with billowing --- +wing_bill = build_wing(distribution=BILLOWING, + billowing_angle=BILLOWING_ANGLE) +body_aero_bill = BodyAerodynamics([wing_bill]) +VortexStepMethod.reinit!(body_aero_bill) + +# --- Build solvers --- +function make_solver(body_aero) + Solver(body_aero; + solver_type=(solver_cfg["solver_type"] == "NONLIN" ? NONLIN : LOOP), + aerodynamic_model_type=getproperty( + VortexStepMethod, + Symbol(solver_cfg["aerodynamic_model_type"])), + density=solver_cfg["density"], + max_iterations=solver_cfg["max_iterations"], + rtol=solver_cfg["rtol"], + tol_reference_error=solver_cfg["tol_reference_error"], + relaxation_factor=solver_cfg["relaxation_factor"], + is_with_artificial_damping=solver_cfg["artificial_damping"], + artificial_damping=(k2=solver_cfg["k2"], k4=solver_cfg["k4"]), + type_initial_gamma_distribution=getproperty( + VortexStepMethod, + Symbol(solver_cfg["type_initial_gamma_distribution"])), + use_gamma_prev=get(solver_cfg, "use_gamma_prev", + get(solver_cfg, "use_gamme_prev", true)), + core_radius_fraction=solver_cfg["core_radius_fraction"], + mu=solver_cfg["mu"], + is_only_f_and_gamma_output=get( + solver_cfg, "calc_only_f_and_gamma", false), + correct_aoa=get(solver_cfg, "correct_aoa", false), + reference_point=get(solver_cfg, "reference_point", + [0.422646, 0.0, 9.3667]), + ) +end + +solver_flat = make_solver(body_aero_flat) +solver_bill = make_solver(body_aero_bill) + +# --- Set flight conditions --- +wind_speed = condition_cfg["wind_speed"] +angle_of_attack_deg = condition_cfg["alpha"] +sideslip_deg = condition_cfg["beta"] + +α0 = deg2rad(angle_of_attack_deg) +β0 = deg2rad(sideslip_deg) +va = wind_speed .* [cos(α0) * cos(β0), sin(β0), sin(α0) * cos(β0)] +set_va!(body_aero_flat, va) +set_va!(body_aero_bill, va) + +# --- Solve and compare --- +results_flat = VortexStepMethod.solve(solver_flat, body_aero_flat; log=true) +results_bill = VortexStepMethod.solve(solver_bill, body_aero_bill; log=true) + +println("\nFlat wing: CL=$(round(results_flat["cl"]; digits=4)), " * + "CD=$(round(results_flat["cd"]; digits=4))") +println("Billowed: CL=$(round(results_bill["cl"]; digits=4)), " * + "CD=$(round(results_bill["cd"]; digits=4))") + +if PLOT + fig1 = plot_combined_analysis( + [solver_flat, solver_bill], + [body_aero_flat, body_aero_bill], + [results_flat, results_bill]; + solver_label=["VSM flat", "VSM billowing"], + labels=labels, + literature_path_list=literature_paths, + angle_range=range(-5, 25, length=31), + angle_type="angle_of_attack", + angle_of_attack=angle_of_attack_deg, + side_slip=sideslip_deg, + v_a=wind_speed, + title="V3 Kite: flat vs billowing " * + "$(round(Int, rad2deg(BILLOWING_ANGLE)))°", + is_show=false, + use_tex=USE_TEX, + angle_of_attack_for_spanwise_distribution=10.0, + ) + scr1 = display(fig1) + isinteractive() && wait(scr1) +end + +nothing diff --git a/src/VortexStepMethod.jl b/src/VortexStepMethod.jl index 965b5ac3..34986627 100644 --- a/src/VortexStepMethod.jl +++ b/src/VortexStepMethod.jl @@ -32,11 +32,11 @@ export BodyAerodynamics export Solver, solve, solve_base!, solve!, VSMSolution, linearize export calculate_results export add_section!, set_va! -export calculate_span, calculate_projected_area +export calculate_span, calculate_projected_area, billowing_angle_from_percentage export MVec3 export Model, VSM, LLT export AeroModel, LEI_AIRFOIL_BREUKELS, POLAR_VECTORS, POLAR_MATRICES, INVISCID -export PanelDistribution, LINEAR, COSINE, SPLIT_PROVIDED, UNCHANGED +export PanelDistribution, LINEAR, COSINE, SPLIT_PROVIDED, UNCHANGED, BILLOWING export InitialGammaDistribution, ELLIPTIC, ZEROS export SolverStatus, FEASIBLE, INFEASIBLE, FAILURE export SolverType, LOOP, NONLIN @@ -121,7 +121,7 @@ where `alpha` is the angle of attack, `delta` is trailing edge angle. end """ - PanelDistribution `LINEAR` `COSINE` `SPLIT_PROVIDED` `UNCHANGED` + PanelDistribution `LINEAR` `COSINE` `SPLIT_PROVIDED` `UNCHANGED` `BILLOWING` Enumeration of the implemented panel distributions. @@ -130,12 +130,14 @@ Enumeration of the implemented panel distributions. - COSINE # Cosine distribution - `SPLIT_PROVIDED` # Split provided sections - `UNCHANGED` # 1:1 copy of unrefined to refined sections (no interpolation) +- `BILLOWING` # Linear distribution with circular arc TE billowing """ @enum PanelDistribution begin LINEAR # Linear distribution COSINE # Cosine distribution SPLIT_PROVIDED # Split provided sections UNCHANGED # 1:1 copy of unrefined to refined sections + BILLOWING # Linear + circular arc TE billowing end """ diff --git a/src/body_aerodynamics.jl b/src/body_aerodynamics.jl index 4cb887dd..7b6c73a8 100644 --- a/src/body_aerodynamics.jl +++ b/src/body_aerodynamics.jl @@ -374,8 +374,9 @@ function calculate_circulation_distribution_elliptical_wing(gamma_i, body_aero:: y[i] = panel.control_point[2] end - # Calculate elliptical distribution - gamma_i .= gamma_0 * sqrt.(1 .- (2 .* y ./ wing_span).^2) + # Calculate elliptical distribution (clamp to avoid sqrt of negative + # when control points lie outside the nominal span envelope) + gamma_i .= gamma_0 * sqrt.(max.(0.0, 1 .- (2 .* y ./ wing_span).^2)) @debug "Calculated circulation distribution: $gamma_i" nothing diff --git a/src/obj_geometry.jl b/src/obj_geometry.jl index 4069a384..2b396d3f 100644 --- a/src/obj_geometry.jl +++ b/src/obj_geometry.jl @@ -580,7 +580,7 @@ function ObjWing( cache = [PreallocationTools.LazyBufferCache()] wing = Wing(n_panels, Int16(n_unrefined_sections), spanwise_distribution, panel_props, MVec3(spanwise_direction), - sections, Section[], remove_nan, use_prior_polar, # refined_sections empty + sections, Section[], remove_nan, use_prior_polar, 0.0, # billowing_angle Int16[], # refined_panel_mapping empty Section[], zeros(n_panels), zeros(n_panels), # non_deformed, theta, delta mass, gamma_tip, inertia_tensor, T_cad_body, R_cad_body, radius, diff --git a/src/settings.jl b/src/settings.jl index 3700ac55..61e740a5 100644 --- a/src/settings.jl +++ b/src/settings.jl @@ -34,6 +34,8 @@ Settings for a single wing, used within [`VSMSettings`](@ref). (default `true`) - `use_prior_polar`: Reuse prior refined/panel polar mapping on reinit/refine updates (default `false`) +- `billowing_angle`: Half-angle of circular arc billowing in radians + (default `0.0`; only used with `BILLOWING` distribution) """ @with_kw mutable struct WingSettings name::String = "main_wing" @@ -45,6 +47,7 @@ Settings for a single wing, used within [`VSMSettings`](@ref). spanwise_direction::MVec3 = [0.0, 1.0, 0.0] remove_nan = true use_prior_polar::Bool = false + billowing_angle::Float64 = 0.0 # half-angle of billowing arc [rad] end """ @@ -170,6 +173,7 @@ function VSMSettings(filename; data_prefix=true) end wing.remove_nan = wing_data["remove_nan"] wing.use_prior_polar = get(wing_data, "use_prior_polar", false) + wing.billowing_angle = get(wing_data, "billowing_angle", 0.0) push!(vsm_settings.wings, wing) n_panels += wing.n_panels diff --git a/src/wing_geometry.jl b/src/wing_geometry.jl index 18d68bbb..9819e35a 100644 --- a/src/wing_geometry.jl +++ b/src/wing_geometry.jl @@ -232,6 +232,7 @@ mutable struct Wing <: AbstractWing refined_sections::Vector{Section} remove_nan::Bool use_prior_polar::Bool + billowing_angle::Float64 # Half-angle of circular arc [rad] (0=straight, π/2=semicircle) # Grouping refined_panel_mapping::Vector{Int16} # Maps each refined panel index to unrefined section index (1 to n_unrefined_sections) @@ -260,7 +261,8 @@ end spanwise_distribution::PanelDistribution=LINEAR, spanwise_direction::PosVector=MVec3([0.0, 1.0, 0.0]), remove_nan::Bool=true, - use_prior_polar::Bool=false) + use_prior_polar::Bool=false, + billowing_angle::Float64=0.0) Constructor for a [Wing](@ref) struct with default values that initializes the sections and refined sections as empty arrays. Creates a basic wing suitable for YAML-based construction. @@ -270,15 +272,17 @@ and refined sections as empty arrays. Creates a basic wing suitable for YAML-bas - `n_unrefined_sections::Int`: Number of unrefined sections (inferred from added sections for YAML wings) - `spanwise_distribution`::PanelDistribution = LINEAR: [PanelDistribution](@ref) - `spanwise_direction::MVec3` = MVec3([0.0, 1.0, 0.0]): Wing span direction vector -- `remove_nan::Bool`: Wether to remove the NaNs from interpolations or not +- `remove_nan::Bool`: Whether to remove the NaNs from interpolations or not - `use_prior_polar::Bool`: Reuse prior refined/panel polar mapping during geometry-only updates +- `billowing_angle::Float64`: Half-angle of billowing arc in radians (0=straight, π/2=semicircle) """ function Wing(n_panels::Int; n_unrefined_sections=nothing, spanwise_distribution::PanelDistribution=LINEAR, spanwise_direction::PosVector=MVec3([0.0, 1.0, 0.0]), remove_nan=true, - use_prior_polar=false) + use_prior_polar=false, + billowing_angle=0.0) # For YAML wings, n_unrefined_sections will be set when sections are added # Set to 0 as placeholder for now @@ -289,7 +293,7 @@ function Wing(n_panels::Int; # Initialize with default/empty values for optional fields Wing( n_panels, n_unrefined_sections_value, spanwise_distribution, panel_props, spanwise_direction, - Section[], Section[], remove_nan, use_prior_polar, + Section[], Section[], remove_nan, use_prior_polar, Float64(billowing_angle), # Grouping Int16[], # Deformation fields @@ -810,6 +814,11 @@ function refine!(wing::AbstractWing; recompute_mapping=true, sort_sections=true) aero_data; reuse_aero_data ) + elseif wing.spanwise_distribution == BILLOWING + refine_mesh_with_billowing!( + wing, LE, TE, aero_model, aero_data; + reuse_aero_data + ) else throw(ArgumentError("Unsupported spanwise panel distribution: $(wing.spanwise_distribution)")) end @@ -1226,6 +1235,159 @@ function refine_mesh_by_splitting_provided_sections!(wing::AbstractWing; reuse_a end +""" + billowing_angle_from_percentage(percentage) + +Compute the billowing half-angle θ (in radians) such that the chord between two +circle intersections is `percentage`% shorter than the minor arc. + +Solves `sin(θ) = θ * (1 - percentage / 100)` using Newton's method. + +# Arguments +- `percentage::Real`: How much shorter the chord is relative to the arc (0–100). + 0 means chord equals arc (θ → 0), ~36.3 means a semicircle (θ = π/2). + +# Returns +- `Float64`: The half-angle θ in radians (same convention as `Wing.billowing_angle`). + +# Example +```julia +julia> rad2deg(billowing_angle_from_percentage(10)) +43.66… +``` +""" +function billowing_angle_from_percentage(percentage::Real) + percentage == 0 && return 0.0 + 0 < percentage || throw(ArgumentError( + "percentage must be ≥ 0, got $percentage")) + percentage < 100 * (1 - 2 / π) || throw(ArgumentError( + "percentage must be < $(100 * (1 - 2/π)) (semicircle limit), " * + "got $percentage")) + factor = 1 - percentage / 100 + # Initial guess from Taylor expansion: sin(θ) ≈ θ - θ³/6 + θ = sqrt(6 * percentage / 100) + for _ in 1:100 + f = sin(θ) - θ * factor + df = cos(θ) - factor + δ = f / df + θ -= δ + abs(δ) < 1e-12 && break + end + return θ +end + +""" + refine_mesh_with_billowing!(wing, LE, TE, aero_model, aero_data; reuse_aero_data) + +Refine wing mesh using linear spacing, then apply circular arc billowing to TE positions. + +Between each pair of unrefined (rib) sections, the trailing edge follows a circular arc +that bulges in the direction perpendicular to the chord and span (simulating fabric +billowing between ribs on a ram-air kite). The leading edge stays linearly interpolated. + +The arc half-angle is `wing.billowing_angle` (0 = straight line, π/2 = semicircle). +""" +function refine_mesh_with_billowing!(wing, LE, TE, aero_model, aero_data; + reuse_aero_data::Bool=false) + n_sections = wing.n_panels + 1 + + # Step 1: Do standard LINEAR refinement first + refine_mesh_for_linear_cosine_distribution!( + wing, 1, LINEAR, n_sections, LE, TE, aero_model, aero_data; + reuse_aero_data + ) + + angle = wing.billowing_angle + if angle ≈ 0.0 + return nothing # No billowing needed + end + + n_unrefined = length(wing.unrefined_sections) + + # Collect unrefined LE positions for rib detection + unrefined_LEs = [s.LE_point for s in wing.unrefined_sections] + + # Iterate over each pair of adjacent unrefined sections (ribs) + for rib_idx in 1:(n_unrefined - 1) + LE_1 = wing.unrefined_sections[rib_idx].LE_point + TE_1 = wing.unrefined_sections[rib_idx].TE_point + LE_2 = wing.unrefined_sections[rib_idx + 1].LE_point + TE_2 = wing.unrefined_sections[rib_idx + 1].TE_point + + # Build local coordinate frame + chord_1 = TE_1 - LE_1 + chord_2 = TE_2 - LE_2 + x_hat = (chord_1 + chord_2) / 2 + x_hat = x_hat / max(norm(x_hat), 1e-12) + + y_vec = LE_1 - LE_2 # spanwise: from section 2 toward section 1 + y_hat = y_vec / max(norm(y_vec), 1e-12) + + z_hat = cross(x_hat, y_hat) + z_hat = z_hat / max(norm(z_hat), 1e-12) + + # Project unrefined TEs into the local yz plane + TE_mid = (TE_1 + TE_2) / 2 + y1 = dot(TE_1 - TE_mid, y_hat) + y2 = dot(TE_2 - TE_mid, y_hat) + d = abs(y1 - y2) # chord length of the arc in yz plane + + if d < 1e-12 + continue # degenerate: both TEs at same spanwise position + end + + # Circular arc parameters + R = (d / 2) / sin(angle) + h = (d / 2) / tan(angle) # center offset from midpoint along z + + # Spanwise extent of this rib pair (for checking membership) + span_len = dot(LE_1 - LE_2, y_hat) + + # Rib chord lengths for interpolation + chord_len_1 = norm(chord_1) + chord_len_2 = norm(chord_2) + + # Displace TE of refined sections that fall between this rib pair + for sec in wing.refined_sections + # Skip sections at any unrefined rib position + is_rib = any(norm(sec.LE_point - ule) < 0.01 for ule in unrefined_LEs) + if is_rib + continue + end + + # Project refined section's LE onto the spanwise direction + frac_vec = sec.LE_point - LE_2 + t = dot(frac_vec, y_hat) / span_len + + # Skip sections outside this rib pair + if t < 0.01 || t > 0.99 + continue + end + + # Arc parametrization: t=1 -> TE_1, t=0 -> TE_2 + # In local coords centered at TE midpoint: + # y(t) = -R * sin(angle * (1 - 2t)) + # z(t) = -h + R * cos(angle * (1 - 2t)) + arc_y = -R * sin(angle * (1 - 2t)) + arc_z = -h + R * cos(angle * (1 - 2t)) + + # Transform arc position back to global coords + arc_TE = TE_mid + arc_y * y_hat + arc_z * z_hat + + # Preserve chord length: use the arc TE to define the chord + # direction, but enforce the interpolated chord length + chord_dir = arc_TE - sec.LE_point + chord_dir_len = norm(chord_dir) + if chord_dir_len > 1e-12 + target_chord = t * chord_len_1 + (1 - t) * chord_len_2 + sec.TE_point .= sec.LE_point + (target_chord / chord_dir_len) * chord_dir + end + end + end + + return nothing +end + """ calculate_span(wing::AbstractWing) diff --git a/src/yaml_geometry.jl b/src/yaml_geometry.jl index 612f85e2..259cdfd2 100644 --- a/src/yaml_geometry.jl +++ b/src/yaml_geometry.jl @@ -150,7 +150,7 @@ end """ Wing(geometry_file::String; n_panels=20, spanwise_distribution=LINEAR, spanwise_direction=[0.0, 1.0, 0.0], remove_nan=true, - use_prior_polar=false, prn=false) + use_prior_polar=false, billowing_angle=0.0, prn=false) Constructs a `Wing` object from a YAML geometry file. @@ -163,6 +163,7 @@ Constructs a `Wing` object from a YAML geometry file. - `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`). - `use_prior_polar::Bool`: Reuse prior refined/panel polar mapping on geometry updates (default: `false`). +- `billowing_angle::Float64`: Half-angle of billowing arc in radians (default: `0.0`). - `prn::Bool`: Print informational messages during construction (default: `false`). # Returns @@ -189,6 +190,7 @@ function Wing( spanwise_direction=[0.0, 1.0, 0.0], remove_nan=true, use_prior_polar=false, + billowing_angle=0.0, prn=false, sort_sections=true ) @@ -243,7 +245,8 @@ function Wing( spanwise_distribution=spanwise_distribution, spanwise_direction=MVec3(spanwise_direction), remove_nan=remove_nan, - use_prior_polar=use_prior_polar + use_prior_polar=use_prior_polar, + billowing_angle=Float64(billowing_angle) ) # Parse sections and populate wing @@ -334,6 +337,7 @@ function Wing(settings::VSMSettings; sort_sections::Bool=true) spanwise_distribution=wing_settings.spanwise_panel_distribution, remove_nan=wing_settings.remove_nan, use_prior_polar=wing_settings.use_prior_polar, + billowing_angle=wing_settings.billowing_angle, sort_sections ) elseif has_obj && has_dat From b38946e50819c696bdc81e5471bde5ecb16d98a2 Mon Sep 17 00:00:00 2001 From: Bart Date: Wed, 18 Mar 2026 16:52:10 +0100 Subject: [PATCH 2/4] Improve plotting legends --- ext/VortexStepMethodMakieExt.jl | 81 ++++++++++++++++++++------------- 1 file changed, 50 insertions(+), 31 deletions(-) diff --git a/ext/VortexStepMethodMakieExt.jl b/ext/VortexStepMethodMakieExt.jl index f159b70c..f58ac56a 100644 --- a/ext/VortexStepMethodMakieExt.jl +++ b/ext/VortexStepMethodMakieExt.jl @@ -555,7 +555,6 @@ function VortexStepMethod.plot_distribution(y_coordinates_list, results_list, la lines!(ax_cl, Vector(y_coords), Vector(results["cl_distribution"]), label="$label CL: $value") end - axislegend(ax_cl, position=:lt) # Plot CD for (y_coords, results, label) in zip(y_coordinates_list, results_list, label_list) @@ -563,35 +562,30 @@ function VortexStepMethod.plot_distribution(y_coordinates_list, results_list, la lines!(ax_cd, Vector(y_coords), Vector(results["cd_distribution"]), label="$label CD: $value") end - axislegend(ax_cd, position=:lt) # Plot Gamma for (y_coords, results, label) in zip(y_coordinates_list, results_list, label_list) lines!(ax_gamma, Vector(y_coords), Vector(results["gamma_distribution"]), label=label) end - axislegend(ax_gamma, position=:lt) # Plot alpha geometric for (y_coords, results, label) in zip(y_coordinates_list, results_list, label_list) lines!(ax_alpha_geo, Vector(y_coords), Vector(results["alpha_geometric"]), label=label) end - axislegend(ax_alpha_geo, position=:lt) # Plot alpha at ac for (y_coords, results, label) in zip(y_coordinates_list, results_list, label_list) lines!(ax_alpha_ac, Vector(y_coords), Vector(results["alpha_at_ac"]), label=label) end - axislegend(ax_alpha_ac, position=:lt) # Plot alpha uncorrected for (y_coords, results, label) in zip(y_coordinates_list, results_list, label_list) lines!(ax_alpha_unc, Vector(y_coords), Vector(results["alpha_uncorrected"]), label=label) end - axislegend(ax_alpha_unc, position=:lt) # Plot force components force_axes = [ax_fx, ax_fy, ax_fz] @@ -607,9 +601,12 @@ function VortexStepMethod.plot_distribution(y_coordinates_list, results_list, la lines!(ax, Vector(y_coords), Vector(forces), label="$label ΣF$comp: $total_force N") end - axislegend(ax, position=:lt) end + # Shared legend at bottom of grid + Legend(fig[4, :], ax_gamma; + orientation=:horizontal, tellwidth=false, tellheight=true) + # Save and show if is_save save_plot(fig, save_path, title, data_type=data_type) @@ -799,7 +796,8 @@ function VortexStepMethod.plot_polars( save_path=nothing, is_save=true, is_show=true, - use_tex=false + use_tex=false, + cl_over_cd=true, ) # Validate inputs total_cases = length(body_aero_list) + length(literature_path_list) @@ -848,8 +846,13 @@ function VortexStepMethod.plot_polars( xlabel="$angle_type [°]", ylabel="CD") ax_cs = Axis(fig[2, 1], title="CS vs $angle_type [°]", xlabel="$angle_type [°]", ylabel="CS") - ax_polar = Axis(fig[2, 2], title="CL vs CD", - xlabel="CD", ylabel="CL") + ax_fourth = if cl_over_cd + Axis(fig[2, 2], title="CL/CD vs $angle_type [°]", + xlabel="$angle_type [°]", ylabel="CL/CD") + else + Axis(fig[2, 2], title="CL vs CD", + xlabel="CD", ylabel="CL") + end # Number of computational results n_solvers = length(solver_list) @@ -864,7 +867,6 @@ function VortexStepMethod.plot_polars( ylims!(ax_cl, -0.5, 2) end end - axislegend(ax_cl, position=:lt) # Plot CD vs angle for (i, (polar_data, label)) in enumerate(zip(polar_data_list, labels_with_re)) @@ -876,7 +878,6 @@ function VortexStepMethod.plot_polars( ylims!(ax_cd, -0.5, 2) end end - axislegend(ax_cd, position=:lt) # Plot CS vs angle for (i, (polar_data, label)) in enumerate(zip(polar_data_list, labels_with_re)) @@ -888,20 +889,28 @@ function VortexStepMethod.plot_polars( ylims!(ax_cs, -0.5, 2) end end - axislegend(ax_cs, position=:lt) - # Plot CL vs CD + # Plot fourth panel: CL/CD vs angle or CL vs CD for (i, (polar_data, label)) in enumerate(zip(polar_data_list, labels_with_re)) marker = i <= n_solvers ? :star5 : :circle markersize = i <= n_solvers ? 12 : 8 - scatterlines!(ax_polar, polar_data[3], polar_data[2]; - label=label, marker=marker, markersize=markersize) - if maximum(polar_data[2]) > 10 || maximum(polar_data[3]) > 10 - ylims!(ax_polar, -0.5, 2) - xlims!(ax_polar, -0.5, 2) + if cl_over_cd + cl_cd = polar_data[2] ./ polar_data[3] + scatterlines!(ax_fourth, polar_data[1], cl_cd; + label=label, marker=marker, markersize=markersize) + else + scatterlines!(ax_fourth, polar_data[3], polar_data[2]; + label=label, marker=marker, markersize=markersize) + if maximum(polar_data[2]) > 10 || maximum(polar_data[3]) > 10 + ylims!(ax_fourth, -0.5, 2) + xlims!(ax_fourth, -0.5, 2) + end end end - axislegend(ax_polar, position=:lt) + + # Shared legend at bottom of grid + Legend(fig[3, :], ax_cl; + orientation=:horizontal, tellwidth=false, tellheight=true) # Save and show if is_save && !isnothing(save_path) @@ -1038,6 +1047,7 @@ function VortexStepMethod.plot_combined_analysis( save_path=nothing, is_save=false, angle_of_attack_for_spanwise_distribution=5.0, + cl_over_cd=true, ) # Normalize inputs to arrays for consistent handling solvers = solver isa Vector ? solver : [solver] @@ -1258,10 +1268,8 @@ function VortexStepMethod.plot_combined_analysis( end end - for ax in [ax_cl, ax_cd, ax_gamma, ax_alpha_geo, ax_alpha_ac, - ax_alpha_unc, ax_fx, ax_fy, ax_fz] - axislegend(ax, position=:lt) - end + Legend(fig[2, 1][4, :], ax_gamma; + orientation=:horizontal, tellwidth=false, tellheight=true) # force y-limits ylims!(ax_alpha_geo, -0.25 * aoa_span, 1.1 * aoa_span) @@ -1323,8 +1331,13 @@ function VortexStepMethod.plot_combined_analysis( xlabel="$angle_type [°]", ylabel="CD") ax_cs_polar = Axis(fig[2, 2][2, 1], title="CS vs $angle_type [°]", xlabel="$angle_type [°]", ylabel="CS") - ax_polar = Axis(fig[2, 2][2, 2], title="CL vs CD", - xlabel="CD", ylabel="CL") + ax_fourth_polar = if cl_over_cd + Axis(fig[2, 2][2, 2], title="CL/CD vs $angle_type [°]", + xlabel="$angle_type [°]", ylabel="CL/CD") + else + Axis(fig[2, 2][2, 2], title="CL vs CD", + xlabel="CD", ylabel="CL") + end for (idx, (pd, lbl)) in enumerate(polar_series) color = colors[mod1(idx, length(colors))] @@ -1334,12 +1347,18 @@ function VortexStepMethod.plot_combined_analysis( scatterlines!(ax_cl_polar, pd.angle, pd.cl; label=lbl, marker, markersize, color) scatterlines!(ax_cd_polar, pd.angle, pd.cd; label=lbl, marker, markersize, color) scatterlines!(ax_cs_polar, pd.angle, pd.cs; label=lbl, marker, markersize, color) - scatterlines!(ax_polar, pd.cd, pd.cl; label=lbl, marker, markersize, color) + if cl_over_cd + cl_cd = pd.cl ./ pd.cd + scatterlines!(ax_fourth_polar, pd.angle, cl_cd; + label=lbl, marker, markersize, color) + else + scatterlines!(ax_fourth_polar, pd.cd, pd.cl; + label=lbl, marker, markersize, color) + end end - # axislegend(ax_cl_polar, position=:lt) - # axislegend(ax_cd_polar, position=:lt) - axislegend(ax_cs_polar, position=:lb) - # axislegend(ax_polar, position=:lt) + Legend(fig[2, 2][3, :], ax_cl_polar; + orientation=:horizontal, nbanks=2, + tellwidth=false, tellheight=true) # Set column widths: left column wider for 3x3 grid colsize!(fig.layout, 1, Relative(0.6)) From 26c5f772143a7a367cb8c800e5e21e8787da3504 Mon Sep 17 00:00:00 2001 From: Bart Date: Wed, 18 Mar 2026 16:58:22 +0100 Subject: [PATCH 3/4] Update docs news and project --- NEWS.md | 17 +++++++++++++++++ Project.toml | 2 +- docs/src/examples.md | 1 + docs/src/functions.md | 1 + 4 files changed, 20 insertions(+), 1 deletion(-) diff --git a/NEWS.md b/NEWS.md index 6ceb5d0d..6c510dab 100644 --- a/NEWS.md +++ b/NEWS.md @@ -1,3 +1,20 @@ +## VortexStepMethod v3.1.0 2026-03-18 + +### Added +- `BILLOWING` panel distribution with circular arc TE billowing between ribs +- `billowing_angle` field on `Wing` and `WingSettings` +- `billowing_angle_from_percentage()` utility function +- `billowing.jl` example comparing flat vs billowed V3 kite +- Coarse V3 kite geometry, settings, and combined CFD polar data +- `cl_over_cd` keyword for `plot_polars` and `plot_combined_analysis` + +### Changed +- Plot legends moved to shared horizontal legend at bottom of grid layouts + +### Fixed +- Domain error in elliptical gamma distribution when control points lie + outside the nominal span envelope + ## VortexStepMethod v3.0.1 2025-03-17 ### Changed - the file `CITATION.cff` diff --git a/Project.toml b/Project.toml index 28ee24a2..80d123c6 100644 --- a/Project.toml +++ b/Project.toml @@ -1,7 +1,7 @@ name = "VortexStepMethod" uuid = "ed3cd733-9f0f-46a9-93e0-89b8d4998dd9" authors = ["1-Bart-1 ", "Oriol Cayon and contributors"] -version = "3.0.1" +version = "3.1.0" [deps] Colors = "5ae59095-9a9b-59fe-a467-6f913c188581" diff --git a/docs/src/examples.md b/docs/src/examples.md index 5327b4ea..6c9d1f8f 100644 --- a/docs/src/examples.md +++ b/docs/src/examples.md @@ -121,6 +121,7 @@ You should see the following menu: ``` Choose function to execute or `q` to quit: > V3_kite = include("V3_kite.jl") + billowing = include("billowing.jl") pyramid_model = include("pyramid_model.jl") rectangular_wing = include("rectangular_wing.jl") ram_air_kite = include("ram_air_kite.jl") diff --git a/docs/src/functions.md b/docs/src/functions.md index 9643987c..f460f967 100644 --- a/docs/src/functions.md +++ b/docs/src/functions.md @@ -8,6 +8,7 @@ refine! calculate_span calculate_projected_area load_polar_data +billowing_angle_from_percentage ``` ## Setting the inflow conditions and solving From 62de74d6ee31b8fa95ad2e403e5ac2e8d54daf35 Mon Sep 17 00:00:00 2001 From: Bart Date: Wed, 18 Mar 2026 17:10:44 +0100 Subject: [PATCH 4/4] Update settings --- data/TUDELFT_V3_KITE/vsm_settings_coarse.yaml | 1 + examples/billowing.jl | 25 +++++++++++++------ src/settings.jl | 25 ++++++++++++++++--- 3 files changed, 40 insertions(+), 11 deletions(-) diff --git a/data/TUDELFT_V3_KITE/vsm_settings_coarse.yaml b/data/TUDELFT_V3_KITE/vsm_settings_coarse.yaml index 4ce8cf66..a65ad638 100644 --- a/data/TUDELFT_V3_KITE/vsm_settings_coarse.yaml +++ b/data/TUDELFT_V3_KITE/vsm_settings_coarse.yaml @@ -50,6 +50,7 @@ wings: spanwise_direction: [0.0, 1.0, 0.0] # Unit vector defining wingspan direction remove_nan: true # Remove NaN values from polar data use_prior_polar: true # Use previously computed polars if available + billowing_angle: 5 # [deg] Half-angle of circular arc billowing # Numerical method settings and convergence criteria solver_settings: diff --git a/examples/billowing.jl b/examples/billowing.jl index 34c9f4e2..33e3d119 100644 --- a/examples/billowing.jl +++ b/examples/billowing.jl @@ -5,7 +5,6 @@ using DelimitedFiles PLOT = true USE_TEX = false -BILLOWING_ANGLE = billowing_angle_from_percentage(5) # Half-angle of billowing arc [rad] # Data paths (all within this repo) project_dir = dirname(dirname(pathof(VortexStepMethod))) @@ -20,6 +19,23 @@ literature_paths = [ joinpath(lit_dir, "python_alpha_sweep.csv"), joinpath(lit_dir, "windtunnel_alpha_sweep_beta_00_0_Poland_2025_Rey_5e5.csv"), ] + +# Load solver settings (coarse: 36 panels, matches 10-section geometry) +settings_data = VortexStepMethod.YAML.load_file( + joinpath(v3_dir, "vsm_settings_coarse.yaml")) +condition_cfg = settings_data["condition"] +solver_cfg = settings_data["solver_settings"] +wing_cfg = settings_data["wings"][1] +n_panels = wing_cfg["n_panels"] + +# Read billowing angle from settings (degrees → radians, or from percentage) +if haskey(wing_cfg, "billowing_percentage") + BILLOWING_ANGLE = billowing_angle_from_percentage( + wing_cfg["billowing_percentage"]) +else + BILLOWING_ANGLE = deg2rad(get(wing_cfg, "billowing_angle", 0.0)) +end + labels = [ "VSM flat", "VSM billowing $(round(Int, rad2deg(BILLOWING_ANGLE)))°", @@ -29,13 +45,6 @@ labels = [ "WindTunnel Re=5e5", ] -# Load solver settings (coarse: 36 panels, matches 10-section geometry) -settings_data = VortexStepMethod.YAML.load_file( - joinpath(v3_dir, "vsm_settings_coarse.yaml")) -condition_cfg = settings_data["condition"] -solver_cfg = settings_data["solver_settings"] -n_panels = settings_data["wings"][1]["n_panels"] - # Load coarse geometry (10 structural rib sections) geom_data = VortexStepMethod.YAML.load_file( joinpath(v3_dir, "aero_geometry_coarse_discretisation.yaml")) diff --git a/src/settings.jl b/src/settings.jl index 61e740a5..df09e232 100644 --- a/src/settings.jl +++ b/src/settings.jl @@ -34,8 +34,13 @@ Settings for a single wing, used within [`VSMSettings`](@ref). (default `true`) - `use_prior_polar`: Reuse prior refined/panel polar mapping on reinit/refine updates (default `false`) -- `billowing_angle`: Half-angle of circular arc billowing in radians - (default `0.0`; only used with `BILLOWING` distribution) +- `billowing_angle`: Half-angle of circular arc billowing in degrees + (default `0.0`; only used with `BILLOWING` distribution). + Converted to radians internally. + Mutually exclusive with `billowing_percentage`. +- `billowing_percentage`: Percentage by which the chord is shorter than + the minor arc (default `nothing`; converted to `billowing_angle`). + Mutually exclusive with `billowing_angle`. """ @with_kw mutable struct WingSettings name::String = "main_wing" @@ -173,7 +178,21 @@ function VSMSettings(filename; data_prefix=true) end wing.remove_nan = wing_data["remove_nan"] wing.use_prior_polar = get(wing_data, "use_prior_polar", false) - wing.billowing_angle = get(wing_data, "billowing_angle", 0.0) + + has_angle = haskey(wing_data, "billowing_angle") + has_pct = haskey(wing_data, "billowing_percentage") + if has_angle && has_pct + throw(ArgumentError( + "Wing '$(wing.name)': specify either " * + "billowing_angle or billowing_percentage, " * + "not both")) + elseif has_pct + wing.billowing_angle = + billowing_angle_from_percentage( + wing_data["billowing_percentage"]) + elseif has_angle + wing.billowing_angle = deg2rad(wing_data["billowing_angle"]) + end push!(vsm_settings.wings, wing) n_panels += wing.n_panels