The moment equation around the center of gravity of the King Air 200 can be derived as follows:
Total moment = Lift moment + Tail moment equation
Lift moment = (Total lift) * (Center of gravity distance)
Tail moment = (Tail lift) * (Tail arm)
Therefore, the moment equation is:
Total moment = (Total lift) * (Center of gravity distance) + (Tail lift) * (Tail arm) + (Aerodynamic center 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 , the tail lift , the centre of gravity distance , the tail arm and the aerodynamic centre moment .
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