Add and use PrecompileTools

Author: ufechner7

Project.toml

@@ -16,6 +16,7 @@ NonlinearSolve = "8913a72c-1f9b-4ce2-8d82-65094dcecaec"
 Parameters = "d96e819e-fc66-5662-9728-84c9c7592b0a"
 Pkg = "44cfe95a-1eb2-52ea-b672-e2afdf69b78f"
 PreallocationTools = "d236fae5-4411-538c-8e31-a6e3d9e00b46"
+PrecompileTools = "aea7be01-6a6a-4083-8856-8a6e6704d82a"
 Serialization = "9e88b42a-f829-5b0c-bbe9-9e923198166b"
 SharedArrays = "1a1011a3-84de-559e-8e89-a11a2f7dc383"
 StaticArrays = "90137ffa-7385-5640-81b9-e52037218182"
@@ -49,6 +50,7 @@ NonlinearSolve = "4"
 Parameters = "0.12"
 Pkg = "1"
 PreallocationTools = "0.4.25"
+PrecompileTools = "1.2.1"
 Serialization = "1"
 SharedArrays = "1"
 StaticArrays = "1"

src/VortexStepMethod.jl

@@ -16,6 +16,7 @@ using Parameters
 using Serialization
 using SharedArrays
 using PreallocationTools
+using PrecompileTools
 using Pkg
 
 # Export public interface
@@ -242,4 +243,44 @@ include("body_aerodynamics.jl")
 include("wake.jl")
 include("solver.jl")
 
+@setup_workload begin
+    # Putting some things in `@setup_workload` instead of `@compile_workload` can reduce the size of the
+    # precompile file and potentially make loading faster.
+    # list = [OtherType("hello"), OtherType("world!")]
+    path = dirname(pathof(@__MODULE__))
+
+    @compile_workload begin
+        # all calls in this block will be precompiled, regardless of whether
+        # they belong to your package or not (on Julia 1.8 and higher)
+        # Step 1: Define wing parameters
+        n_panels = 20          # Number of panels
+        span = 20.0            # Wing span [m]
+        chord = 1.0            # Chord length [m]
+        v_a = 20.0             # Magnitude of inflow velocity [m/s]
+        density = 1.225        # Air density [kg/m³]
+        alpha_deg = 30.0       # Angle of attack [degrees]
+        alpha = deg2rad(alpha_deg)
+
+        # Step 2: Create wing geometry with linear panel distribution
+        wing = Wing(n_panels, spanwise_panel_distribution=LINEAR)
+
+        # Add wing sections - defining only tip sections with inviscid airfoil model
+        add_section!(wing, 
+            [0.0, span/2, 0.0],    # Left tip LE 
+            [chord, span/2, 0.0],  # Left tip TE
+            INVISCID)
+        add_section!(wing, 
+            [0.0, -span/2, 0.0],   # Right tip LE
+            [chord, -span/2, 0.0], # Right tip TE
+            INVISCID)
+
+        # Step 3: Initialize aerodynamics
+        body_aero::BodyAerodynamics = BodyAerodynamics([wing])
+
+        y = [panel.control_point[2] for panel in body_aero.panels]
+
+        nothing
+    end
+end
+
 end # module

src/wing_geometry.jl

@@ -236,7 +236,7 @@ function refine_aerodynamic_mesh!(wing::AbstractWing)
         return nothing
     end
 
-    @info "Refining aerodynamic mesh from $(length(wing.sections)) sections to $n_sections sections."
+    @debug "Refining aerodynamic mesh from $(length(wing.sections)) sections to $n_sections sections."
 
     # Handle two-section case
     if n_sections == 2