VortexStepMethod.jl/examples/stall_model.jl at fd8829c452b2d3c6dda61930c4fc7f6b5da0e8c7 · OpenSourceAWE/VortexStepMethod.jl · GitHub

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using Pkg
Pkg.activate(@__DIR__)

using GLMakie
using LinearAlgebra
using VortexStepMethod

using CSV
using DataFrames

PLOT = true
USE_TEX = false

# Find root directory
root_dir = dirname(@__DIR__)
save_folder = joinpath(root_dir, "results", "TUDELFT_V3_KITE")
mkpath(save_folder)

# Defining discretisation
n_panels = 54
spanwise_distribution = SPLIT_PROVIDED

# Load rib data from CSV
csv_file_path = joinpath(
    root_dir,
    "data",
    "TUDELFT_V3_KITE",
    "rib_list_from_CAD_LE_TE_and_surfplan_d_tube_camber_19ribs.csv"
)

df = CSV.read(csv_file_path, DataFrame)
rib_list = []
for row in eachrow(df)
    LE = [row.LE_x, row.LE_y, row.LE_z]
    TE = [row.TE_x, row.TE_y, row.TE_z]
    push!(rib_list, (LE, TE, LEI_AIRFOIL_BREUKELS, (row.d_tube, row.camber)))
end

# Create wing geometry
# n_unrefined_sections will be automatically set to the number of ribs (18 sections)
CAD_wing = Wing(n_panels; spanwise_distribution)
for rib in rib_list
    add_section!(CAD_wing, rib[1], rib[2], rib[3], rib[4])
end
refine!(CAD_wing)
body_aero = BodyAerodynamics([CAD_wing])

# Create solvers
vsm_solver = Solver(body_aero;
    aerodynamic_model_type=VSM,
    is_with_artificial_damping=false
)
VSM_with_stall_correction = Solver(body_aero;
    aerodynamic_model_type=VSM,
    is_with_artificial_damping=true
)

# Setting velocity conditions
v_a = 15.0
aoa = 17.0
side_slip = 0.0
yaw_rate = 0.0
aoa_rad = deg2rad(aoa)
vel_app = [
    cos(aoa_rad) * cos(side_slip),
    sin(side_slip),
    sin(aoa_rad)
] * v_a
set_va!(body_aero, vel_app)

# Solve both configurations
results = solve(vsm_solver, body_aero)
@time results_with_stall = solve(VSM_with_stall_correction, body_aero)
@time results_with_stall = solve(VSM_with_stall_correction, body_aero)

# Setup literature data paths
path_cfd_lebesque = joinpath(
    root_dir,
    "data",
    "TUDELFT_V3_KITE",
    "literature_results",
    "V3_CL_CD_RANS_Lebesque_2024_Rey_300e4.csv"
)

# Only include literature data if file exists
literature_paths = isfile(path_cfd_lebesque) ? [path_cfd_lebesque] : String[]

# Plot combined analysis
PLOT && plot_combined_analysis(
    [vsm_solver, VSM_with_stall_correction],
    [body_aero, body_aero],
    [results, results_with_stall];
    solver_label=["VSM", "VSM (with stall)"],
    literature_path_list=literature_paths,
    angle_range=range(0, 25, length=25),
    angle_type="angle_of_attack",
    angle_of_attack=aoa,
    side_slip=side_slip,
    v_a=v_a,
    title="Stall Model Comparison",
    is_show=true,
    use_tex=USE_TEX
)
nothing