Ive read a lot of things here on RCU trying to figure this out, but how do you find the CG of a biplane? The plane is somewhat scratch built, although it started life as a BUSA flybaby. After several apparent crashes, things are not as they once were. I have no plans, etc for this model (even if i did, i dont know that they would be much help). Im not an aerodynamic engineer so alot of the explantions are way over my head. I downloaded some software called CMEI that allows me to find the Mean Aerodynamic Chord (whats this?) of a single wing, but what about a double wing? It also seems to need the CG to use? Well, I dont know the CG.. =) Can someone explain in plain english how to go about figuring this out? Another thing I have noticed is that it seems that the actual fuselage has no bearing on determining the CG. Is it based entirely on the wing structure? I really appreciate any input you guys can give me here. I am at a loss!
The calculator I used gave me these results:
Sweep Distance @ MAC (C) = 1
Mean Aerodynamic Chord (MAC) = 8
MAC Distance from Root (d) = 21.5
Balance Point @ Root Chord (CG) = 3

Is the the Balance point the CG? Is that 3 inches from the trailing or leading edge? Also MOST IMPORTANT this is a BIPLANE. So could someone please help me and explain in plain english? So is the CG in the calculation measured on the upper wing or lower wing? Does the stagger effect the cg? I have been to all the calculators and they are no help to me since I dont understand what they mean and none so far have applied to bipes. Links to more calculators honestly, while thoughtful, are pretty useless to me.
Brice D