make more use of MVec3

Author: ufechner7

src/body_aerodynamics.jl

@@ -105,20 +105,20 @@ end
 Structure to hold calculated panel properties.
 
 # Fields
-- `aero_centers`::Vector{PosVector}
-- `control_points`::Vector{PosVector}
-- `bound_points_1`::Vector{PosVector}
-- `bound_points_2`::Vector{PosVector}
+- `aero_centers`::Vector{MVec3}
+- `control_points`::Vector{MVec3}
+- `bound_points_1`::Vector{MVec3}
+- `bound_points_2`::Vector{MVec3}
 - `x_airf`::Vector{Vector{Float64}}: unclear, please define
 - `y_airf`::Vector{Vector{Float64}}: unclear, please define
 - `z_airf`::Vector{Vector{Float64}}: unclear, please define
 
 """
 struct PanelProperties
-    aero_centers::Vector{PosVector}
-    control_points::Vector{PosVector}
-    bound_points_1::Vector{PosVector}
-    bound_points_2::Vector{PosVector}
+    aero_centers::Vector{MVec3}
+    control_points::Vector{MVec3}
+    bound_points_1::Vector{MVec3}
+    bound_points_2::Vector{MVec3}
     x_airf::Vector{Vector{Float64}}
     y_airf::Vector{Vector{Float64}}
     z_airf::Vector{Vector{Float64}}

src/kite_geometry.jl

@@ -177,7 +177,7 @@ Represents a curved wing that inherits from Wing with additional geometric prope
 - All fields from Wing:
   - `n_panels::Int`: Number of panels in aerodynamic mesh
   - `spanwise_panel_distribution::String`: Panel distribution type
-  - `spanwise_direction::Vector{Float64}`: Wing span direction vector
+  - `spanwise_direction::MVec3`: Wing span direction vector
   - `sections::Vector{Section}`: List of wing sections
 - Additional fields:
   - `center_of_mass::Vector{Float64}`: Center of mass coordinates
@@ -190,7 +190,7 @@ Same as Wing
 mutable struct KiteWing <: AbstractWing
     n_panels::Int64
     spanwise_panel_distribution::String
-    spanwise_direction::Vector{Float64}
+    spanwise_direction::MVec3
     sections::Vector{Section}
 
     # Additional fields for KiteWing

src/panel.jl

@@ -11,7 +11,7 @@ Represents a panel in a vortex step method simulation.
 - `TE_point_2::Vector{MVec3}`: Second trailing edge point
 - `LE_point_2::Vector{MVec3}`: Second leading edge point
 - `chord::Float64`: Panel chord length
-- `va::Union{Nothing,Vector{Float64}}`: Panel velocity
+- `va::Union{Nothing, MVec3}`: Panel velocity
 - `corner_points::Matrix{Float64}`: Panel corner points
 - `aero_model::String`: Aerodynamic model type
 - `aerodynamic_center::Vector{Float64}`: Panel aerodynamic center
@@ -30,7 +30,7 @@ mutable struct Panel{P}
     TE_point_2::MVec3
     LE_point_2::MVec3
     chord::Float64
-    va::Union{Nothing,Vector{Float64}}
+    va::Union{Nothing, MVec3}
     corner_points::Matrix{Float64}
     aero_model::String
     cl_coefficients::Union{Nothing,Vector{Float64}}

src/solver.jl

@@ -24,18 +24,18 @@ struct Solver
     is_only_f_and_gamma_output::Bool
 
     function Solver(;
-        aerodynamic_model_type::String="VSM",
-        density::Float64=1.225,
-        max_iterations::Int64=1500,
-        allowed_error::Float64=1e-5,
-        tol_reference_error::Float64=0.001,
-        relaxation_factor::Float64=0.03,
-        is_with_artificial_damping::Bool=false,
+        aerodynamic_model_type::String   = "VSM",
+        density::Float64                 = 1.225,
+        max_iterations::Int64            = 1500,
+        allowed_error::Float64           = 1e-5,
+        tol_reference_error::Float64     = 0.001,
+        relaxation_factor::Float64       = 0.03,
+        is_with_artificial_damping::Bool = false,
         artificial_damping::NamedTuple{(:k2, :k4), Tuple{Float64, Float64}}=(k2=0.1, k4=0.0),
         type_initial_gamma_distribution::String="elliptic",
-        core_radius_fraction::Float64=1e-20,
-        mu::Float64=1.81e-5,
-        is_only_f_and_gamma_output::Bool=false
+        core_radius_fraction::Float64    = 1e-20,
+        mu::Float64                      = 1.81e-5, # TODO do not use magic constants
+        is_only_f_and_gamma_output::Bool = false
     )
         new(
             aerodynamic_model_type,

src/wing_geometry.jl

@@ -5,21 +5,21 @@
 Represents a wing section with leading edge, trailing edge, and aerodynamic properties.
 
 # Fields
-- `LE_point::Vector{Float64}`: Leading edge point coordinates
-- `TE_point::Vector{Float64}`: Trailing edge point coordinates
+- `LE_point::MVec3`: Leading edge point coordinates
+- `TE_point::MVec3`: Trailing edge point coordinates
 - `aero_input::Vector{Any}`: Aerodynamic input data for the section:
     - `("inviscid")`: Inviscid aerodynamics
     - `("polar_data", [alpha_column,CL_column,CD_column,CM_column])`: Polar data aerodynamics
     - `("lei_airfoil_breukels", [d_tube,camber])`: LEI airfoil with Breukels parameters
 """
 struct Section{T}
-    LE_point::Vector{Float64}
-    TE_point::Vector{Float64}
+    LE_point::MVec3
+    TE_point::MVec3
     aero_input::T
 
     function Section(
-            LE_point::Vector{Float64}, 
-            TE_point::Vector{Float64}, 
+            LE_point::PosVector, 
+            TE_point::PosVector, 
             aero_input::T
             ) where T
         new{T}(LE_point, TE_point, aero_input)