I was wondering how engineers go about determining the CoG of an aircraft. I know how to find the CoG for standard shapes and composite areas using double integrals and what not, but there has to be a more efficient way for engineers to go about doing this.
From my knowledge the CoG is supposed to be at the center of the wings. Is this correct. Also if the CoG is poorly located, does this just result in an unstable aircraft that requires constant control input?
From my knowledge the CoG is supposed to be at the center of the wings. Is this correct. Also if the CoG is poorly located, does this just result in an unstable aircraft that requires constant control input?