Calculating wing angle of attack

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Calculating wing angle of attack

Postby 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. :roll:


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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