Add back types

Author: 1-Bart-1

docs/src/types.md

@@ -28,7 +28,7 @@ A body is constructed of one or more abstract wings. An abstract wing can be a W
 A Wing/ RamAirWing has one or more sections.
 ```@docs
 Section
-Section(LE_point, TE_point, aero_model)
+Section(LE_point::PosVector, TE_point::PosVector, aero_model)
 Wing
 Wing(n_panels::Int; spanwise_distribution::PanelDistribution=LINEAR,
      spanwise_direction::PosVector=MVec3([0.0, 1.0, 0.0]))

src/body_aerodynamics.jl

@@ -1,23 +1,25 @@
 """
     @with_kw mutable struct BodyAerodynamics{P}
 
-Main structure for calculating aerodynamic properties of bodies.
+Main structure for calculating aerodynamic properties of bodies. Use the constructor to initialize.
 
 # Fields
 - panels::Vector{Panel}: Vector of [Panel](@ref) structs
 - wings::Union{Vector{Wing}, Vector{RamAirWing}}: A vector of wings; a body can have multiple wings
-- `_va`::MVec3 = zeros(MVec3):   A vector of the apparent wind speed, see: [MVec3](@ref)
+- `va::MVec3` = zeros(MVec3):   A vector of the apparent wind speed, see: [MVec3](@ref)
 - `omega`::MVec3 = zeros(MVec3): A vector of the turn rates around the kite body axes
 - `gamma_distribution`=zeros(Float64, P): A vector of the circulation 
                         of the velocity field; Length: Number of segments. [m²/s]
 - `alpha_uncorrected`=zeros(Float64, P): angles of attack per panel
 - `alpha_corrected`=zeros(Float64, P):   corrected angles of attack per panel
 - `stall_angle_list`=zeros(Float64, P):  stall angle per panel
-- `alpha_array` = zeros(Float64, P)
-- `v_a_array` = zeros(Float64, P)
+- `alpha_array::MVector{P, Float64}` = zeros(Float64, P)
+- `v_a_array::MVector{P, 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]
+- `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]
+- `y::MVector{P, Float64}` = zeros(MVector{P, Float64})
+- `cache::Vector{PreallocationTools.LazyBufferCache{typeof(identity), typeof(identity)}}` = [LazyBufferCache() for _ in 1:5]
 """
 @with_kw mutable struct BodyAerodynamics{P}
     panels::Vector{Panel}
@@ -43,6 +45,9 @@ end
 
 Construct a [BodyAerodynamics](@ref) object for aerodynamic calculations.
 
+This constructor handles initialization of panels, coordinate transformations, and
+aerodynamic properties, returning a fully initialized structure ready for simulation.
+
 # Arguments
 - `wings::Vector{T}`: Vector of wings to analyze, where T is an AbstractWing type
 
@@ -53,6 +58,12 @@ Construct a [BodyAerodynamics](@ref) object for aerodynamic calculations.
 
 # Returns
 - [BodyAerodynamics](@ref) object initialized with panels and wings
+
+# Example
+```julia
+wing = RamAirWing("body.obj", "foil.dat")
+body_aero = BodyAerodynamics([wing], va=[15.0, 0.0, 0.0], omega=zeros(3))
+```
 """
 function BodyAerodynamics(
     wings::Vector{T};
@@ -304,7 +315,7 @@ end
 Update angle of attack at aerodynamic center for VSM method.
 
 Returns:
-    Vector{Float64}: Updated angles of attack
+    nothing
 """
 function update_effective_angle_of_attack!(alpha_corrected,
     body_aero::BodyAerodynamics, 

src/wing_geometry.jl

@@ -18,14 +18,14 @@ Represents a wing section with leading edge, trailing edge, and aerodynamic prop
 end
 
 """
-    Section(LE_point, TE_point, aero_model)
+    Section(LE_point::PosVector, TE_point::PosVector, aero_model)
 
 Create a new wing section with the specified leading edge point, trailing edge point, 
 and aerodynamic model.
 
 # Arguments
-- `LE_point::MVec3`: Leading edge point coordinates
-- `TE_point::MVec3`: Trailing edge point coordinates  
+- `LE_point::PosVector`: Leading edge point coordinates
+- `TE_point::PosVector`: Trailing edge point coordinates  
 - `aero_model::AeroModel`: Aerodynamic model type (e.g., INVISCID, POLAR_VECTORS)
 
 # Returns
@@ -36,11 +36,11 @@ function Section(LE_point, TE_point, aero_model)
 end
 
 """
-    init!(section::Section, LE_point, TE_point, aero_model=nothing, aero_data=nothing)
+    init!(section::Section, LE_point::PosVector, TE_point::PosVector, aero_model=nothing, aero_data=nothing)
 
 Function to update a [Section](@ref) in place.
 """
-function init!(section::Section, LE_point::AbstractVector, TE_point::AbstractVector, aero_model=nothing, aero_data=nothing)
+function init!(section::Section, LE_point, TE_point, aero_model=nothing, aero_data=nothing)
     section.LE_point .= LE_point
     section.TE_point .= TE_point
     (!isnothing(aero_model)) && (section.aero_model = aero_model)

test/bench.jl

@@ -116,7 +116,7 @@ using LinearAlgebra
             z_airf_array[i, :] .= panel.z_airf
         end
 
-        alphas = collect(-20:30)
+        alphas = collect(-20.0:30.0)
         cls = [2π * α for α in alphas]
         cds = [0.01 + 0.05 * α^2 for α in alphas]
         cms = [-0.1 * α for α in alphas]