A few wind tunnel experiments conducted on a wing-body shape (with a wing area S of 0.25 m, and a chord c of 0.2 m), have resulted in the following data: Lift curve slope, a Aerodynamic center location, ha : 0.075 deg : 0.25 Coefficient of moment about the aero-center : -0.03 Zero-lift downwash angle, & : 0 deg Downwash angle slope, : 0.25 deg A horizontal stabilizer/tail (with no elevator) with a plan area S, of 0.025 m and a lift curve slope a; of 0.1/deg, has been determined to be located with 1, = 0.2m. and i, = 8.625 deg. For a cg location h = 0.2, answer the following: a. Is the vehicle statically balanced? b. Determine the location of the neutral point (in fractions of chord). c. Is it statically stable? d. Determine its static margin. e. At what angle of attack can the vehicle be trimmed (remember there is no elevator)