Originally posted by Tall Paul
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Close... I like to know what the fixed values are in addition to which of them are variable.
The c.g. in the "wing" section is 18%.
12.3% (negative) for the "canard" section..
40% in the "power" section
and 37% in "glider"..
but apparently the option to change isn't part of the sheet.
I'd prefer that option.
Tall Paul
Here are the equations that are used to calculate the CG for the flying wing. They were derived from equations published originally by Ron Van Putte, June1980, Model Aviation and then they were used in a Basic program printed in Soar Tech.
CG = P + ACw
P = (R^2 + (R X T) + T^2)/(15(T + R))
R = Wing Root Chord
T = Wing Tip Chord
The CG in % MACw is calculated for each combination of variables.
I hope this helps.
Alan