



What's the model?






you might try this: (for Flying Wings)
Q = (R x R) + (R x T) + (T x T) divided by 6(R + T) P = R + 2T divided by 3(R + T) D = Q + SP WHERE R = Root Chord measurement T = Tip Chord measurement S = Sweepback of the leading edge measured at the tip D = The distance back from the tip of the nose to the point of balance(c.g.). AND where the core is standard shape and has a straight leading edge. (i.e. not curved) This comes pretty close (I found this formula in an article written by Jef Raskin) Luke 

Last edited by sylair; Jun 08, 2004 at 11:30 AM.




http://www.coloradogliders.com/tools.htm
Use the CG calc at 1520% @ the MAC Balance Point. 

Last edited by omega blood; Jun 08, 2004 at 02:31 AM.
