Fix test

Author: 1-Bart-1

src/body_aerodynamics.jl

@@ -13,11 +13,11 @@ Main structure for calculating aerodynamic properties of bodies.
 - `alpha_uncorrected`::Vector{Float64}=zeros(Float64, P): angles of attack per panel
 - `alpha_corrected`::Vector{Float64}=zeros(Float64, P):   corrected angles of attack per panel
 - `stall_angle_list`::Vector{Float64}=zeros(Float64, P):  stall angle per panel
-- alpha_array::Vector{Float64} = zeros(Float64, P)
-- v_a_array::Vector{Float64} = zeros(Float64, P)
-- work_vectors::NTuple{10, MVec3} = ntuple(_ -> zeros(MVec3), 10)
+- `alpha_array`::Vector{Float64} = zeros(Float64, P)
+- `v_a_array`::Vector{Float64} = zeros(Float64, P)
+- `work_vectors`::NTuple{10, MVec3} = ntuple(_ -> zeros(MVec3), 10)
 - AIC::Array{Float64, 3} = zeros(3, P, P)
-- projected_area::Float64 = 1.0: The area projected onto the xy-plane of the kite body reference frame [m²]
+- `projected_area`::Float64 = 1.0: The area projected onto the xy-plane of the kite body reference frame [m²]
 """
 @with_kw mutable struct BodyAerodynamics{P}
     panels::Vector{Panel}

test/bench.jl

@@ -29,7 +29,7 @@ using LinearAlgebra
     alpha_deg = 30.0       # Angle of attack [degrees]
     alpha = deg2rad(alpha_deg)
 
-    wing = Wing(n_panels, spanwise_distribution=LINEAR)
+    wing = Wing(n_panels, spanwise_distribution=UNCHANGED)
     add_section!(wing, 
         [0.0, span/2, 0.0],    # Left tip LE 
         [chord, span/2, 0.0],  # Left tip TE
@@ -43,7 +43,8 @@ using LinearAlgebra
     init!(body_aero)
 
     @testset "Re-initialization" begin
-        result = @benchmark init!(body_aero; init_aero=false) samples=1 evals=1
+        init_aero=false
+        result = @benchmark init!($body_aero; init_aero=$init_aero) samples=1 evals=1
         @info "Re-initializing Allocations: $(result.allocs) \t Memory: $(result.memory)"
         @test result.allocs < 100
     end