From bb17e29e10efb02f44602fe5f9412ba84d930331 Mon Sep 17 00:00:00 2001
From: Andy Killorin <37423245+Speedy6451@users.noreply.github.com>
Date: Wed, 1 Nov 2023 09:48:01 -0500
Subject: [PATCH] switched to a less cambered airfoil (used in the element 2)

---
 Makefile    | 5 ++++-
 src/main.rs | 8 ++++----
 2 files changed, 8 insertions(+), 5 deletions(-)

diff --git a/Makefile b/Makefile
index c01972e..4a68698 100644
--- a/Makefile
+++ b/Makefile
@@ -1,12 +1,15 @@
 build: build/allparts.svg
 
-build/%.scad: e393.dat edgevertical.dat src/*.rs
+build/%.scad: ag24.dat edgevertical.dat src/*.rs
 	mkdir -p build
 	cargo run
 
 e393.dat:
 	curl http://airfoiltools.com/airfoil/seligdatfile?airfoil=e393-il -o e393.dat
 
+ag24.dat:
+	curl https://m-selig.ae.illinois.edu/ads/coord/ag24.dat -o ag24.dat
+
 edgevertical.zip:
 	curl "https://www.rcgroups.com/forums/showatt.php?attachmentid=2973018&d=1262752423" -o edgevertical.zip
 
diff --git a/src/main.rs b/src/main.rs
index 01dad80..5cd0acb 100644
--- a/src/main.rs
+++ b/src/main.rs
@@ -16,16 +16,16 @@ fn main() {
     scad_file.set_detail(50);
 
     // cambered airfoil, used in the wing
-    let e393: Airfoil = selig::parse(include_str!("../e393.dat"));
+    let wing_airfoil: Airfoil = selig::parse(include_str!("../ag24.dat"));
 
     // symetric airfoil, used in the control surfaces
-    let evert: Airfoil = selig::parse(include_str!("../edgevertical.dat"));
+    let control_airfoil: Airfoil = selig::parse(include_str!("../edgevertical.dat"));
 
     let mut wing_transform = scad!(Translate(vec3(0.0,0.0,0.0)));
 
     // struts
     for port in [true,false] {
-        let mut wing = wing(&e393, STRUTS/2, WINGSPAN/2.0, CHORD, CHORD * 0.8);
+        let mut wing = wing(&wing_airfoil, STRUTS/2, WINGSPAN/2.0, CHORD, CHORD * 0.8);
         wing = scad!(Translate(vec3(0.0, 10.0,0.0)); wing);
         if port {
             wing = scad!(Mirror(vec3(0.0, 1.0, 0.0)); wing);
@@ -38,7 +38,7 @@ fn main() {
 
     // rudder
     let mut rudder = scad!(Rotate(90.0, vec3(1.0, 0.0, 0.0)));
-    rudder.add_child(wing(&evert, RUDDER_STRUTS, RUDDER_HEIGHT, RUDDER_CHORD, RUDDER_CHORD * RUDDER_TAPER));
+    rudder.add_child(wing(&control_airfoil, RUDDER_STRUTS, RUDDER_HEIGHT, RUDDER_CHORD, RUDDER_CHORD * RUDDER_TAPER));
 
     scad_file.add_object(rudder);