Rectangular Wing

Wing Aerodynamics Analysis using Vortex-Step Method (VSM) and Lift Line Theory (LLT)

This example demonstrates the process of setting up and analyzing a wing's aerodynamics using VSM and LLT. We'll cover the following steps:

1. Importing necessary libraries.
2. Define the wing parameters
3. Create wing geometry with linear panel distribution and add the wing sections
4. Initializing the wing aerodynamics and set the inflow conditions.
5. Initialize solvers for both LLT and VSM methods
6. Running a simulation with both methods
7. Plotting combined analysis

First, install Julia and set up the examples environment as explained in the section Running the examples as developer. Then launch Julia:

julia --project=examples

Step 1: Importing the necessary libraries:

julia> using LinearAlgebra
julia> using GLMakie
julia> using VortexStepMethod

Step 2: Define wing parameters

julia> n_panels = 20          # Number of panels
julia> span = 20.0            # Wing span [m]
julia> chord = 1.0            # Chord length [m]
julia> v_a = 20.0             # Magnitude of inflow velocity [m/s]
julia> alpha_deg = 30.0       # Angle of attack [degrees]
julia> alpha = deg2rad(alpha_deg)

Step 3: Create wing geometry with linear panel distribution

julia> wing = Wing(n_panels, spanwise_distribution=LINEAR)

Add wing sections - defining only tip sections with inviscid airfoil model

julia> add_section!(wing,
           [0.0, span/2, 0.0],   # Left tip LE
           [chord, span/2, 0.0],  # Left tip TE
           INVISCID)
julia> add_section!(wing,
           [0.0, -span/2, 0.0],  # Right tip LE
           [chord, -span/2, 0.0], # Right tip TE
           INVISCID)

Refine the mesh

julia> refine!(wing)

Step 4: Initialize aerodynamics

julia> body_aero = BodyAerodynamics([wing])

We need to pass here an array of wing objects, because a body can have multiple wings.

Set inflow conditions

julia> vel_app = [cos(alpha), 0.0, sin(alpha)] .* v_a
julia> set_va!(body_aero, vel_app, [0, 0, 0.1])

Step 5: Initialize solvers for both LLT and VSM methods

julia> llt_solver = Solver(body_aero; aerodynamic_model_type=LLT)
julia> vsm_solver = Solver(body_aero; aerodynamic_model_type=VSM)

Step 6: Solve using both methods

julia> results_llt = solve(llt_solver, body_aero)
julia> results_vsm = solve(vsm_solver, body_aero)

Print results comparison

julia> println("\nLifting Line Theory Results:")
julia> println("CL = $(round(results_llt["cl"], digits=4))")
julia> println("CD = $(round(results_llt["cd"], digits=4))")
julia> println("\nVortex Step Method Results:")
julia> println("CL = $(round(results_vsm["cl"], digits=4))")
julia> println("CD = $(round(results_vsm["cd"], digits=4))")
julia> println("Projected area = $(round(results_vsm["projected_area"], digits=4)) m²")

Step 7: Plot combined analysis

julia> angle_range = range(0, 20, 20)
julia> plot_combined_analysis(
           [llt_solver, vsm_solver],
           [body_aero, body_aero],
           [results_llt, results_vsm];
           solver_label=["LLT", "VSM"],
           angle_range=angle_range,
           angle_type="angle_of_attack",
           v_a=v_a,
           title="Rectangular Wing",
           is_show=true,
       )

More examples

From the examples environment (julia --project=examples), you can execute more examples by typing:

julia> include("examples/menu.jl")

You should see the following menu:

Choose function to execute or `q` to quit:
 > 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")
   cleanup = include("cleanup.jl")
   quit

You can select one of the examples using the <UP> and <DOWN> keys. Press <ENTER> to run the selected example.