The form shown below will calculate the position of the Center of Gravity (CG) of a model airplane wing as measured from the leading edge of the Root Chord.

Enter Root Chord (A):
Enter Tip Chord (B):
Enter Sweep Distance (S):
Enter Half Span (Y):
Enter %MAC Balance Point:
Sweep Distance @ MAC (C) =
Mean Aerodynamic Chord (MAC) =
MAC Distance from Root (d) =
Balance Point @ Root Chord (CG) =

The Equations

C	= (S(A+2B)) / (3(A+B))
MAC	= A-(2(A-B)(0.5A+B) / (3(A+B)))
d	= (2Y(0.5A+B)) / (3(A+B))
CG	= %MAC B.P.*(MAC) + C

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