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An experimental wing design is mounted in a wind tunnel. The test wing area and chord are 6.6 m? and 1.05 m, respectively. Flow conditions for all tests are set for an altitude of 12000 m and a -7'-=**-- ~* V,, = 900 km/hr. The lift slope of the wing is Main Content % measured at a = 0.06 ! and the moment coefficient about the aerodynamic center is Cy. = 0.002. The absolute angle of attack is a, = 6 and the center of gravity is located at h = 0.44 chord and the aerodynamic center is located at h,,. = 0.39 chord. A fixed (no elevator) horizontal tail is attached /, = 2.48 m from the airplane's center of gravity with a tail area of S,= 1.68 m?. The tail-setting angle is i, = 2.2 and its lift slope is a,= 0.09! and the zero-lift downwash angle is = 0 and d2/da = 0.36. Determine the Moment about the center of gravity (M,,). (Hint: See Examples 7.3 and 7.4; Homework Problems 7.2 and 7.4) C) Mg =15501 N C) Mg = 62080 N C) M,g = 18890 N CO) Meg = ~4912 N