public void TestAirfoil()
{
Airfoil airfoil = Airfoil.Get("NACA0012");
Assert.AreEqual(0.755, airfoil.CL(-165), 0.01);
Assert.AreEqual(0.256, airfoil.CD(-165), 0.01);
Assert.AreEqual(0.326, airfoil.CM(-165), 0.01);
}
public override void Update(double dt)
{
var normalizedVelocity = Velocity.Normalize(2);
var alpha = Math.Atan2(normalizedVelocity.z(), normalizedVelocity.x());
var CL = airfoil.CL(alpha * 180.0 / Math.PI);
var CD = airfoil.CD(alpha * 180.0 / Math.PI);
var CM = airfoil.CM(alpha * 180.0 / Math.PI);
var V2 = Velocity.Norm(2);
var L = 0.5 * Density * V2 * span * CL;
var D = 0.5 * Density * V2 * span * CD;
var M = 0.5 * Density * V2 * span * chord * CM;
Force = Vector <double> .Build.DenseOfArray(new double[] {
-D *Math.Cos(alpha) + L *Math.Sin(alpha),
0,
-L *Math.Cos(alpha) - D *Math.Sin(alpha)
});
Torque = Vector <double> .Build.DenseOfArray(new double[] { 0, M, 0 });
}
