refactoring

src/filament.jl

@@ -6,7 +6,7 @@ abstract type Filament end
 
 # Constants for all filament types
 const ALPHA0 = 1.25643  # Oseen parameter
-const NU = 1.48e-5     # Kinematic viscosity of air
+const NU = 1.48e-5      # Kinematic viscosity of air
 
 """
     BoundFilament
@@ -152,10 +152,10 @@ end
 Represents a semi-infinite vortex filament.
 """
 struct SemiInfiniteFilament <: Filament
-    x1::Vector{Float64}         # Starting point
-    direction::Vector{Float64}  # Direction vector
+    x1::MVec3                  # Starting point
+    direction::MVec3           # Direction vector
     vel_mag::Float64           # Velocity magnitude
-    filament_direction::Int    # Direction indicator (-1 or 1)
+    filament_direction::Int64  # Direction indicator (-1 or 1)
 end
 
 """

src/kite_geometry.jl

@@ -14,7 +14,7 @@ function read_faces(filename)
             elseif startswith(line, "f ")
                 parts = split(line)
                 # Handle both f v1 v2 v3 and f v1/vt1/vn1 v2/vt2/vn2 v3/vt3/vn3 formats
-                indices = map(p -> parse(Int, split(p, '/')[1]), parts[2:4])
+                indices = map(p -> parse(Int64, split(p, '/')[1]), parts[2:4])
                 push!(faces, indices)
             end
         end
@@ -175,7 +175,7 @@ Represents a curved wing that inherits from Wing with additional geometric prope
 
 # Fields
 - All fields from Wing:
-  - `n_panels::Int`: Number of panels in aerodynamic mesh
+  - `n_panels::Int64`: Number of panels in aerodynamic mesh
   - `spanwise_panel_distribution::String`: Panel distribution type
   - `spanwise_direction::Vector{Float64}`: Wing span direction vector
   - `sections::Vector{Section}`: List of wing sections
@@ -188,7 +188,7 @@ Represents a curved wing that inherits from Wing with additional geometric prope
 Same as Wing
 """
 mutable struct KiteWing <: AbstractWing
-    n_panels::Int
+    n_panels::Int64
     spanwise_panel_distribution::String
     spanwise_direction::Vector{Float64}
     sections::Vector{Section}

src/panel.jl

@@ -178,7 +178,7 @@ function compute_lei_coefficients(section_1::Section, section_2::Section)
     )
 
     # Compute S values
-    S = Dict{Int,Float64}()
+    S = Dict{Int64,Float64}()
     S[9] = C[20]*t^2 + C[21]*t + C[22]
     S[10] = C[23]*t^2 + C[24]*t + C[25]
     S[11] = C[26]*t^2 + C[27]*t + C[28]

src/plotting.jl

@@ -630,7 +630,7 @@ function plot_polars(
         )
         push!(polar_data_list, polar_data)
         # Update label with Reynolds number
-        label_list[i] = "$(label_list[i]) Re = $(round(Int, rey*1e-5))e5"
+        label_list[i] = "$(label_list[i]) Re = $(round(Int64, rey*1e-5))e5"
     end
 
     # Load literature data if provided

src/solver.jl

@@ -8,7 +8,7 @@ struct Solver
     # General settings
     aerodynamic_model_type::String
     density::Float64
-    max_iterations::Int
+    max_iterations::Int64
     allowed_error::Float64
     tol_reference_error::Float64
     relaxation_factor::Float64
@@ -26,7 +26,7 @@ struct Solver
     function Solver(;
         aerodynamic_model_type::String="VSM",
         density::Float64=1.225,
-        max_iterations::Int=1500,
+        max_iterations::Int64=1500,
         allowed_error::Float64=1e-5,
         tol_reference_error::Float64=0.001,
         relaxation_factor::Float64=0.03,

src/wing_aerodynamics.jl

@@ -129,15 +129,15 @@ struct PanelProperties
 end
 
 """
-    calculate_panel_properties(section_list::Vector{Section}, n_panels::Int,
+    calculate_panel_properties(section_list::Vector{Section}, n_panels::Int64,
                              aero_center_loc::Float64, control_point_loc::Float64)
 
 Calculate geometric properties for each panel.
 
 Returns:
     PanelProperties containing vectors for each property
 """
-function calculate_panel_properties(section_list::Vector{Section}, n_panels::Int,
+function calculate_panel_properties(section_list::Vector{Section}, n_panels::Int64,
                                   aero_center_loc::Float64, control_point_loc::Float64)
     # Initialize arrays
     aero_centers = Vector{Float64}[]

src/wing_geometry.jl

@@ -32,7 +32,7 @@ end
 Represents a wing composed of multiple sections with aerodynamic properties.
 
 # Fields
-- `n_panels::Int`: Number of panels in aerodynamic mesh
+- `n_panels::Int64`: Number of panels in aerodynamic mesh
 - `spanwise_panel_distribution::String`: Panel distribution type
 - `spanwise_direction::Vector{Float64}`: Wing span direction vector
 - `sections::Vector{Section}`: List of wing sections
@@ -45,12 +45,12 @@ Represents a wing composed of multiple sections with aerodynamic properties.
 - "unchanged": Keep original sections
 """
 mutable struct Wing <: AbstractWing
-    n_panels::Int
+    n_panels::Int64
     spanwise_panel_distribution::String
     spanwise_direction::PosVector
     sections::Vector{Section}
 
-    function Wing(n_panels::Int;
+    function Wing(n_panels::Int64;
                  spanwise_panel_distribution::String="linear",
                  spanwise_direction::PosVector=MVec3([0.0, 1.0, 0.0]))
         new(n_panels, 
@@ -183,14 +183,14 @@ end
 
 """
     calculate_new_aero_input(aero_input::Vector{Any}, 
-                            section_index::Int,
+                            section_index::Int64,
                             left_weight::Float64,
                             right_weight::Float64)
 
 Interpolate aerodynamic input between two sections.
 """
 function calculate_new_aero_input(aero_input, 
-                                section_index::Int,
+                                section_index::Int64,
                                 left_weight::Float64,
                                 right_weight::Float64)
 
@@ -266,7 +266,7 @@ end
 """
     refine_mesh_for_linear_cosine_distribution(
         spanwise_panel_distribution::String,
-        n_sections::Int,
+        n_sections::Int64,
         LE::Matrix{Float64},
         TE::Matrix{Float64},
         aero_input::Vector{Any})
@@ -285,7 +285,7 @@ Returns:
 """
 function refine_mesh_for_linear_cosine_distribution(
     spanwise_panel_distribution::String,
-    n_sections::Int,
+    n_sections::Int64,
     LE,
     TE,
     aero_input)

test/utils.jl

@@ -8,7 +8,7 @@ include("thesis_oriol_cayon.jl")
 """
 Create an array with cosine spacing, from min to max values, with n points
 """
-function cosspace(min_val::Real, max_val::Real, n_points::Int)
+function cosspace(min_val::Real, max_val::Real, n_points::Int64)
     mean_val = (max_val + min_val) / 2
     amp = (max_val - min_val) / 2
     return mean_val .+ amp .* cos.(range(π, 0, length=n_points))
@@ -22,7 +22,7 @@ Generate 3D coordinates of a rectangular wing with twist and dihedral.
 - `span::Float64`: Total wing span
 - `twist::Vector{Float64}`: Twist angles in radians
 - `beta::Vector{Float64}`: Dihedral angles in radians
-- `N::Int`: Number of spanwise panels
+- `N::Int64`: Number of spanwise panels
 - `dist::String`: Distribution type ("cos" or "lin")
 
 # Returns
@@ -61,7 +61,7 @@ Generate 3D coordinates of a curved wing.
 - `span::Float64`: Wing span
 - `theta::Float64`: Angular extent of curvature (radians)
 - `R::Float64`: Radius of curvature
-- `N::Int`: Number of spanwise panels
+- `N::Int64`: Number of spanwise panels
 - `dist::String`: Distribution type ("cos", "lin", or "cos2")
 
 # Returns
@@ -94,7 +94,7 @@ Generate 3D coordinates of an elliptical wing.
 # Arguments
 - `max_chord::Float64`: Maximum chord length
 - `span::Float64`: Wing span
-- `N::Int`: Number of spanwise panels
+- `N::Int64`: Number of spanwise panels
 - `dist::String`: Distribution type ("cos" or "lin")
 
 # Returns