The moment equation around the centre of gravity of the King Air 200 can be derived as follows:
M_cg = (L × l_cg) - (L_H × l_H) - M_ac
Where:
M_cg = Moment around the centre of gravity
L = Total lift
l_cg = Centre of gravity distance
L_H = Tail lift
l_H = Tail arm
M_ac = Aerodynamic centre moment
In the picture below you see a King Air 200, an aircraft with a so-called T-tail. One of the primary reasons of placing the tail higher up is to keep the tail out of the wake and downwash of the wing. Here, you may assume that . Image courtesy of Mark Jones Jr., CC - BY For this aircraft, we will in this exercise investigate the required position of the centre of gravity to guarantee static, longitudinal stability. The first step in this analysis is to set up the moment equation around the centre of gravity of this aircraft. 1. Derive the moment equation around the centre of gravity of this King Air 200, as a function of the total lift L , the tail lift L_H, the centre of gravity distance l_cg, the tail arm l_H and the aerodynamic centre moment M_ac .
1 answer
1 answer