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Add V3_kite.jl
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‎examples_cp/V3_kite.jl‎

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using Pkg
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if !("ControlPlots" ∈ keys(Pkg.project().dependencies))
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Pkg.activate(@__DIR__)
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end
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using LinearAlgebra
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using VortexStepMethod
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using ControlPlots
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PLOT = true
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USE_TEX = false
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DEFORM = false
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project_dir = dirname(@__DIR__)
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literature_paths = [
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joinpath(project_dir, "data", "TUDELFT_V3_KITE", "literature_results", "CFD_RANS_Rey_5e5_Poland2025_alpha_sweep_beta_0_NoStruts.csv"),
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joinpath(project_dir, "data", "TUDELFT_V3_KITE", "literature_results", "CFD_RANS_Rey_10e5_Poland2025_alpha_sweep_beta_0.csv"),
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joinpath(project_dir, "data", "TUDELFT_V3_KITE", "literature_results", "python_alpha_sweep.csv"),
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joinpath(project_dir, "data", "TUDELFT_V3_KITE", "literature_results", "windtunnel_alpha_sweep_beta_00_0_Poland_2025_Rey_5e5.csv"),
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]
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labels = [
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"VSM Julia Re=5e5",
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"CFD Re=5e5",
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"CFD Re=10e5", #with struts
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"VSM Python Re=5e5",
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"WindTunnel Re=5e5" #with struts
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]
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beta_literature_paths = [
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joinpath(project_dir, "data", "TUDELFT_V3_KITE", "literature_results", "windtunnel_beta_sweep_alpha_07_4_Poland_2025_Rey_5e5.csv"),
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# joinpath(project_dir, "data", "TUDELFT_V3_KITE", "literature_results", "windtunnel_beta_sweep_alpha_12_5_Poland_2025_Rey_5e5.csv"),
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]
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beta_labels = [
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labels[1],
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"Wind Tunnel Re=5e5 beta sweep alpha=7.4",
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# "Wind Tunnel Re=5e5 beta sweep alpha=12.5",
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]
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# Load YAML settings directly (avoids VSMSettings(filename) conversion issues in live sessions)
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settings_path = joinpath(project_dir, "data", "TUDELFT_V3_KITE", "vsm_settings.yaml")
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settings_data = VortexStepMethod.YAML.load_file(settings_path)
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condition_cfg = settings_data["condition"]
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wing_cfg = settings_data["wings"][1]
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solver_cfg = settings_data["solver_settings"]
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# Create wing, body_aero, and solver objects using settings
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wing = Wing(
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joinpath(project_dir, wing_cfg["geometry_file"]);
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n_panels=wing_cfg["n_panels"],
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spanwise_distribution=getproperty(VortexStepMethod, Symbol(wing_cfg["spanwise_panel_distribution"])),
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spanwise_direction=Float64.(wing_cfg["spanwise_direction"]),
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remove_nan=wing_cfg["remove_nan"],
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)
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refine!(wing)
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body_aero = BodyAerodynamics([wing])
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VortexStepMethod.reinit!(body_aero)
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if DEFORM
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VortexStepMethod.unrefined_deform!(
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wing,
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deg2rad.(range(-10, 10, length=wing.n_unrefined_sections)),
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deg2rad.(range(0, 0, length=wing.n_unrefined_sections));
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smooth=true
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)
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VortexStepMethod.reinit!(body_aero; init_aero=false)
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end
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# Construct Solver using keyword arguments from solver settings
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solver = Solver(body_aero;
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solver_type=(solver_cfg["solver_type"] == "NONLIN" ? NONLIN : LOOP),
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aerodynamic_model_type=getproperty(VortexStepMethod, Symbol(solver_cfg["aerodynamic_model_type"])),
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density=solver_cfg["density"],
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max_iterations=solver_cfg["max_iterations"],
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rtol=solver_cfg["rtol"],
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tol_reference_error=solver_cfg["tol_reference_error"],
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relaxation_factor=solver_cfg["relaxation_factor"],
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is_with_artificial_damping=solver_cfg["artificial_damping"],
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artificial_damping=(k2=solver_cfg["k2"], k4=solver_cfg["k4"]),
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type_initial_gamma_distribution=getproperty(VortexStepMethod, Symbol(solver_cfg["type_initial_gamma_distribution"])),
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use_gamma_prev=get(solver_cfg, "use_gamma_prev", get(solver_cfg, "use_gamme_prev", true)),
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core_radius_fraction=solver_cfg["core_radius_fraction"],
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mu=solver_cfg["mu"],
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is_only_f_and_gamma_output=get(solver_cfg, "calc_only_f_and_gamma", false),
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correct_aoa=get(solver_cfg, "correct_aoa", false),
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reference_point=get(solver_cfg, "reference_point", [0.422646, 0.0, 9.3667]), #ref-point from WT exp.
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)
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# Extract values for plotting (optional - for reference)
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wind_speed = condition_cfg["wind_speed"]
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angle_of_attack_deg = condition_cfg["alpha"]
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sideslip_deg = condition_cfg["beta"]
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yaw_rate = condition_cfg["yaw_rate"]
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# Set flight conditions from settings
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α0 = deg2rad(angle_of_attack_deg)
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β0 = deg2rad(sideslip_deg)
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set_va!(body_aero, wind_speed .* [cos(α0) * cos(β0), sin(β0), sin(α0) * cos(β0)])
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# Solve and plot combined analysis
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results = VortexStepMethod.solve(solver, body_aero; log=true)
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# Plotting polars
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PLOT && plot_polars(
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[solver],
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[body_aero],
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labels,
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literature_path_list=literature_paths,
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angle_range=range(-5, 25, length=31),
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angle_type="angle_of_attack",
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angle_of_attack=angle_of_attack_deg,
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side_slip=sideslip_deg,
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v_a=wind_speed,
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title="$(wing.n_panels)_panels_$(wing.spanwise_distribution)_from_yaml_settings",
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data_type=".pdf",
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is_save=false,
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is_show=true,
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use_tex=USE_TEX
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)
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# Plotting geometry
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results = VortexStepMethod.solve(solver, body_aero; log=true)
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PLOT && plot_geometry(
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body_aero,
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"";
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data_type=".svg",
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save_path="",
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is_save=false,
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is_show=true,
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view_elevation=15,
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view_azimuth=-120,
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use_tex=USE_TEX
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)
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# Plotting spanwise distributions
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body_y_coordinates = [panel.aero_center[2] for panel in body_aero.panels]
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PLOT && plot_distribution(
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[body_y_coordinates],
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[results],
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["VSM"];
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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))",
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data_type=".pdf",
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is_save=false,
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is_show=true,
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use_tex=USE_TEX
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)
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nothing

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