1. Consider a fixed-wing General Aviation aircraft-shown below-with a maximum takeoff weight of 2200 lb, a wing planform area of 162 ft, and the following characteristics (Fig. 3.14): de 1 1 da = 0.32; CLawf 5.7 = rad CLan = 4.3 ;; b = 31 ft; nh rad 0.96; Sh = = 38 ft Determine longitudinally static statically derivative; Cma, neutral point position (np), and static margin (SM). Is this aircraft longitudinally statically stable?