Non-allocating init pos

Author: 1-Bart-1

examples/ram_air_kite.jl

@@ -9,6 +9,8 @@ DEFORM = true
 # Create wing geometry
 wing = RamAirWing("data/ram_air_kite_body.obj", "data/ram_air_kite_foil.dat")
 body_aero = BodyAerodynamics([wing];)
+println("First init")
+@time VortexStepMethod.init!(body_aero)
 
 if DEFORM
     # Linear interpolation of alpha from 10° at one tip to 0° at the other
@@ -19,8 +21,10 @@ if DEFORM
     delta_end = deg2rad(0)
     theta_dist = [theta_start - i * (theta_start - theta_end)/(n_panels-1) for i in 0:(n_panels-1)]
     delta_dist = [delta_start - i * (delta_start - delta_end)/(n_panels-1) for i in 0:(n_panels-1)]
+    println("Deform")
     @time VortexStepMethod.deform!(wing, theta_dist, delta_dist)
-    @time VortexStepMethod.init!(body_aero)
+    println("Deform init")
+    @time VortexStepMethod.init!(body_aero; init_aero=false)
 end
 
 # Create solvers

src/body_aerodynamics.jl

@@ -89,14 +89,16 @@ Initialize a BodyAerodynamics struct in-place by setting up panels and coefficie
 # Arguments
 - `body_aero::BodyAerodynamics`: The structure to initialize
 
+# Keyword Arguments
+- `init_aero::Bool`: Wether to initialize the aero data or not
+
 # Returns
 nothing
 """
-function init!(body_aero::BodyAerodynamics)
-
+function init!(body_aero::BodyAerodynamics; init_aero=true)
     idx = 1
+    vec = zeros(MVec3)
     for wing in body_aero.wings
-        println("init wing")
         init!(wing)
         panel_props = wing.panel_props
 
@@ -118,8 +120,10 @@ function init!(body_aero::BodyAerodynamics)
                 panel_props.x_airf[i, :],
                 panel_props.y_airf[i, :],
                 panel_props.z_airf[i, :],
-                delta;
-                remove_nan=wing.remove_nan
+                delta,
+                vec;
+                remove_nan=wing.remove_nan,
+                init_aero
             )
             idx += 1
         end

src/filament.jl

@@ -28,10 +28,11 @@ Represents a bound vortex filament defined by two points.
     initialized::Bool = false
 end
 
-function init!(filament::BoundFilament, x1::PosVector, x2::PosVector)
+function init!(filament::BoundFilament, x1::PosVector, x2::PosVector, vec=zeros(MVec3))
     filament.x1 .= x1
     filament.x2 .= x2
-    filament.length = norm(x2 - x1)
+    vec .= x2 .- x1
+    filament.length = norm(vec)
     filament.r0 .= x2 .- x1
     filament.initialized = true
     return nothing

src/panel.jl

@@ -84,7 +84,8 @@ function init_pos!(
     x_airf::PosVector,
     y_airf::PosVector,
     z_airf::PosVector,
-    delta
+    delta,
+    vec::MVec3
 )
     # Initialize basic geometry
     panel.TE_point_1 .= section_1.TE_point
@@ -95,11 +96,15 @@ function init_pos!(
         norm(panel.TE_point_1 - panel.LE_point_1) +
         norm(panel.TE_point_2 - panel.LE_point_2)
     ) / 2
-    panel.corner_points .= hcat(panel.LE_point_1, panel.TE_point_1, panel.TE_point_2, panel.LE_point_2)
-    panel.width = norm(bound_point_2 - bound_point_1)
-    init!(panel.filaments[1], bound_point_2, bound_point_1)
-    init!(panel.filaments[2], bound_point_1, panel.TE_point_1)
-    init!(panel.filaments[3], panel.TE_point_2, bound_point_2)
+    panel.corner_points[:, 1] = panel.LE_point_1
+    panel.corner_points[:, 2] = panel.TE_point_1
+    panel.corner_points[:, 3] = panel.TE_point_2
+    panel.corner_points[:, 4] = panel.LE_point_2
+    vec .= bound_point_2 .- bound_point_1
+    panel.width = norm(vec)
+    init!(panel.filaments[1], bound_point_2, bound_point_1, vec)
+    init!(panel.filaments[2], bound_point_1, panel.TE_point_1, vec)
+    init!(panel.filaments[3], panel.TE_point_2, bound_point_2, vec)
 
     panel.bound_point_1 .= bound_point_1
     panel.bound_point_2 .= bound_point_2
@@ -190,12 +195,13 @@ function init!(
     x_airf::PosVector,
     y_airf::PosVector,
     z_airf::PosVector,
-    delta;
+    delta,
+    vec::MVec3;
     init_aero = true,
     remove_nan = true
 )
-    init_pos!(panel, section_1, section_2, aero_center, control_point, bound_point_1, bound_point_2,
-        x_airf, y_airf, z_airf, delta)
+    @time init_pos!(panel, section_1, section_2, aero_center, control_point, bound_point_1, bound_point_2,
+        x_airf, y_airf, z_airf, delta, vec)
     init_aero && init_aero!(panel, section_1, section_2; remove_nan)
     return nothing
 end

src/wing_geometry.jl

@@ -233,7 +233,7 @@ function init!(wing::AbstractWing)
     refine_aerodynamic_mesh!(wing)
 
     # Calculate panel properties
-    @time update_panel_properties!(
+    update_panel_properties!(
         wing.panel_props,
         wing.refined_sections,
         wing.n_panels