A place to discuss everything related to Newton Dynamics.
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by PJani » Fri Aug 27, 2010 12:45 pm
Hy guys i am trying to calculate wing angle of attack. I have wing normal , their center of mass and velocity of fuselage.
This is my lift curve(angle of atack is in radians)...i calculated this polynomial from points.
- Code: Select all
struct SubF
{
static dFloat liftCurve(dFloat x)
{
if(x>-0.087 && x<0.521)
return -13432.556f
* (-0.52151586f + x)
* (0.087f + x)
* (0.092538092f + x)
* (0.20620989f + (-0.84661103f + x)* x)
* (0.047291951f + (-0.15885782f +x)* x);
return 0.0;
}
};
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PJani
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