Load airfoils at runtime

Makefile

@@ -1,3 +1,7 @@
+MAIN_AIRFOIL    = ag24.dat
+CONTROL_AIRFOIL = m1-il.dat
+TAIL            = t-tail
+
 UNAME = $(shell uname)
 ifeq ($(UNAME), Linux)
 	SCAD = openscad
@@ -6,8 +10,7 @@ ifeq ($(UNAME), Darwin)
 	SCAD = OpenSCAD
 endif
 
-AIRFOILS = ag24.dat m1-il.dat
+AIRFOILS = $(MAIN_AIRFOIL) $(CONTROL_AIRFOIL)
-TAIL = t-tail
 
 b: build/allparts.svg
 
@@ -16,15 +19,15 @@ build:
 
 build/assembly.scad: src/*.rs $(AIRFOILS)
 	mkdir -p build
-	cargo run $(TAIL) assembly
+	cargo run $(AIRFOILS) $(TAIL) assembly
 
 build/part%.scad: src/*.rs $(AIRFOILS)
 	mkdir -p build
-	cargo run parts $(TAIL)
+	cargo run $(AIRFOILS) parts $(TAIL)
 
 build/allparts.scad: src/*.rs $(AIRFOILS)
 	mkdir -p build
-	cargo run sheet $(TAIL)
+	cargo run $(AIRFOILS) sheet $(TAIL)
 
 e393.dat:
 	curl http://airfoiltools.com/airfoil/seligdatfile?airfoil=e393-il -o e393.dat
@@ -46,7 +49,7 @@ edgevertical.dat: edgevertical.zip
 	unzip -p edgevertical.zip Edge-Vertical.dat > edgevertical.dat
 
 build/%.png:  build/%.scad
-	$(SCAD) --colorscheme Metallic -o $@ $<
+	$(SCAD) --imgsize 1920,1080 --colorscheme Metallic -o $@ $<
 
 build/%.svg:  build/%.scad
 	$(SCAD) -o $@ $<
@@ -73,20 +76,20 @@ clean:
 	cargo clean
 
 vis: build/assembly-clear.scad
-	openscad build/assembly-clear.scad
+	$(SCAD) build/assembly-clear.scad
 
 v-tail: src/*.rs $(AIRFOILS)
-	cargo run v-tail assembly sheet parts
+	cargo run $(AIRFOILS) v-tail assembly sheet parts
 
 t-tail: src/*.rs $(AIRFOILS)
-	cargo run t-tail assembly sheet parts
+	cargo run $(AIRFOILS) t-tail assembly sheet parts
 
 build/testwing-clear.scad: build/testwing.scad
 	sed 's/color("clear-red")/color([1.0,1.0,0.0,0.9])/g' $< > $@
 	sed 's/color("clear-blue")/color([0.0,1.0,1.0,1.0])/g' -i $@
 
 build/assembly-clear.scad: src/*.rs $(AIRFOILS)
-	cargo run assembly $(TAIL) film stdout |\
+	cargo run $(AIRFOILS) assembly $(TAIL) film stdout |\
 	sed 's/color("clear-red")/color([1.0,0.0,0.0,0.5])/g' |\
 	sed 's/color("clear-blue")/color([0.0,1.0,0.0,0.9])/g' |\
 	sed 's/color("clear-blue")/color([0.0,0.0,1.0,0.9])/g' > $@

src/main.rs

@@ -4,12 +4,18 @@ use scad::*;
 use selig::SeligFile;
 use selig::Span;
 use std::env::args;
+use std::path::Path;
 use std::ops::Range;
 mod constants;
 mod selig;
 
 fn main() {
-    let args: Vec<String> = args().collect();
+    let mut args = args().skip(1);
+    let main_airfoil_path = args.next().unwrap();
+    let main_airfoil_path = Path::new(&main_airfoil_path);
+    let control_airfoil_path = args.next().unwrap();
+    let control_airfoil_path = Path::new(&control_airfoil_path);
+    let args: Vec<String> = args.collect();
     let gen_film = args.contains(&"film".to_string());
     let gen_v_tail = args.contains(&"v-tail".to_string());
     let gen_t_tail = args.contains(&"t-tail".to_string());
@@ -25,10 +31,18 @@ fn main() {
     scad_file.set_detail(50);
 
     // cambered airfoil, used in the wing
-    let wing_airfoil: SeligFile = SeligFile::parse(include_str!("../ag24.dat"));
+    let wing_airfoil: SeligFile = SeligFile::load(main_airfoil_path).unwrap();
+    eprintln!("Main airfoil: {}", wing_airfoil.get_name());
+    if let Some(desc) = wing_airfoil.get_description() {
+        eprintln!("{}", desc);
+    }
 
     // symmetric airfoil, used in the control surfaces
-    let control_airfoil: SeligFile = SeligFile::parse(include_str!("../m1-il.dat"));
+    let control_airfoil: SeligFile = SeligFile::load(control_airfoil_path).unwrap();
+    eprintln!("Control airfoil: {}", control_airfoil.get_name());
+    if let Some(desc) = control_airfoil.get_description() {
+        eprintln!("{}", desc);
+    }
 
     // main wing
     let mut wing_transform = mirrored_wing(&wing_airfoil, &WING);

src/selig.rs

@@ -1,4 +1,5 @@
-use std::ops::Range;
+use std::{ops::Range, path::Path, fs::File, io::Read};
+use std::io;
 
 use nalgebra::Vector2;
 
@@ -37,6 +38,12 @@ impl SeligFile {
         }
     }
 
+    pub fn load(path: &Path) -> io::Result<Self> {
+        let mut buf = String::new();
+        File::open(path)?.read_to_string(&mut buf)?;
+        io::Result::Ok(Self::parse(&buf))
+    }
+
     pub fn get_points(&self) -> &Airfoil {
         &self.data
     }