WK95
Well-Known Member
Assuming for an aerodynamic center at 25% of the MAC and a conventional aircraft, a common starting point for the C.G. range is between 25% and 32% of the MAC. This means that since the center of lift is in front of the CG and generating lift, the tail must also generate upwards lift to resist pitching up.
On the other hand, other some other resources indicate that the CG is located in front of center of lift such that in most flight conditions, the the tail generates a down load to resist a pitch down tendency.
So then, in light of this apparently conflicting information, where should I locate the CG for a conventional aircraft relative to the wing aerodynamic center? And why is the information differing between different sources on aircraft design and stability analysis?
On the other hand, other some other resources indicate that the CG is located in front of center of lift such that in most flight conditions, the the tail generates a down load to resist a pitch down tendency.
So then, in light of this apparently conflicting information, where should I locate the CG for a conventional aircraft relative to the wing aerodynamic center? And why is the information differing between different sources on aircraft design and stability analysis?