Figure P.13.3 shows the flight envelope at sea-level for an aircraft with a wing span of 27.5m, average wing chord 3.05m, and total weight 196kN. The aerodynamic center is 0.915 m forward of the center of gravity and the center of lift for the tail is 16.7m aft of the center of gravity (assume that the tail does not produce any aerodynamic moment). The pitching moment coefficient (about the aerodynamic center) is C_M,0 = ?0.0638 (where positive is nose-up).

We are also given the following information about the rear half of the aircraft: If we take a cut of the aircraft passing through its center of gravity, the center of gravity of this portion of the aircraft is 5.7m aft of the cut. Given, the weight of this portion of the aircraft is 98kN. You may neglect aerodynamic loads on the rear portion of the aircraft, with the exception of the lift generated by the tail.

1. Considering the flight condition labeled by the point marked A in the V-n diagram. Determine the total lift generated by the main wing, the aerodynamic moment at the aerodynamic center and the lift generated by the tail. Use the d'Alambert approach. Now for parts b-c consider internal results in the fuselage at the Body Station location at the center of gravity of the complete aircraft.

a.c. CG tail center of lift N 0.915m 16.7m CUT is 5.7m location of c.g. of complete aircraft .c.g of rear half of plane 3.5 1.0 -1.0 Cruise point 25 V m/s 61.0 91.5 152.5 183 Fig. P.13.3