Consider an aircraft with the following characteristics... S = Wing Horizontal Stabilizer 232.00 [ft2] S =...

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Consider an aircraft with the following characteristics... S = Wing Horizontal Stabilizer 232.00 [ft2] S = 54.00 [ft] c = 7.04 [ft] c = 3.83 [ft] ac/le = 4.07 [ft] Mac/le = 2.79 [ft] xle = 16.40 [ft] i = CLO 1.00 [deg] -0.0443 = -0.0175 CLa = 5.0800 CLO CLa = xle = 0.0000 = 4.2600 36.90 [ft] = 0.0000 CLoet = 1.8000 0 = 0.642 [deg] = 0.426 n = 0.9 where... . The wing and horizontal stabilizer are trapezoidal surfaces. The cg of the aircraft is at xcg = 10.56 [ft]. The weight of the aircraft is W = 9,500 [lb]. The propulsive moment coefficients are CMo, = 0.0 and CMop . = 0.0. The fuselage moment coefficients are CMo = 0.0 and CMa = 0.0. The horizontal tail incidence can only be set between 0.5 and 7 [deg]. a. Determine the trim conditions when the aircraft is descending from 5,000 ft above sea level at a speed of 210 knots on a 3-degree glidepath (a flight path angle of -3 degrees) when... i. the aircraft in its "clean" configuration, i.e., when the characteristics of the wing are as given above. ii. the flaps and landing gears of the aircraft are extended, i.e., when C = 0.1000. b. Explain why, because the propulsive moment coefficients are zero, we don't have to consider the increase in drag and the resulting moment due to increased thrust in our computations. c. Explain how you would go about solving the problem for an aircraft where the thrust vector does not pass through the center of gravity. Consider an aircraft with the following characteristics... S = Wing Horizontal Stabilizer 232.00 [ft2] S = 54.00 [ft] c = 7.04 [ft] c = 3.83 [ft] ac/le = 4.07 [ft] Mac/le = 2.79 [ft] xle = 16.40 [ft] i = CLO 1.00 [deg] -0.0443 = -0.0175 CLa = 5.0800 CLO CLa = xle = 0.0000 = 4.2600 36.90 [ft] = 0.0000 CLoet = 1.8000 0 = 0.642 [deg] = 0.426 n = 0.9 where... . The wing and horizontal stabilizer are trapezoidal surfaces. The cg of the aircraft is at xcg = 10.56 [ft]. The weight of the aircraft is W = 9,500 [lb]. The propulsive moment coefficients are CMo, = 0.0 and CMop . = 0.0. The fuselage moment coefficients are CMo = 0.0 and CMa = 0.0. The horizontal tail incidence can only be set between 0.5 and 7 [deg]. a. Determine the trim conditions when the aircraft is descending from 5,000 ft above sea level at a speed of 210 knots on a 3-degree glidepath (a flight path angle of -3 degrees) when... i. the aircraft in its "clean" configuration, i.e., when the characteristics of the wing are as given above. ii. the flaps and landing gears of the aircraft are extended, i.e., when C = 0.1000. b. Explain why, because the propulsive moment coefficients are zero, we don't have to consider the increase in drag and the resulting moment due to increased thrust in our computations. c. Explain how you would go about solving the problem for an aircraft where the thrust vector does not pass through the center of gravity.