Consider an infinite flat plate of aircraft at 15 angle of attack in a Mach of...

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Consider an infinite flat plate of aircraft at 15° angle of attack in a Mach of 9 at an altitude of 60 km. Assume span length of 1 m. i. Sketch shock waves and expansion fan and streamline passing through the flat plate. (1 point) Also, draw the lift and drag forces on the plate. (1 point) Calculate the Mach number, temperature, density, pressure, total temperature, total pressure on top surface of plate. (1.5 point) Calculate the Mach number, temperature, density, pressure, total temperature, total pressure on the botttom surface of plate. (1.5 point) Calculate the lift and drag forces. (1 point) Calculate lift and drag coefficients. (1 point); Also, calculate the lift-to-drag ratio. (1 point) ii. iii. iv. V. vi. vii. h m 0 1000 2000 3000 4000 5000 6000 7000 8000 9000 10000 15000 20000 25000 30000 40000 50000 60000 70000 80000 km 0 1 2 3 4 LO 5 LO 6 7 8 10 15 20 25 30 40 50 60 70 80 T C 15 8.5 2 -4.49 -10.98 -17.47 -23.96 -30.45 -36.94 -43.42 -49.9 -56.5 -56.5 -51.6 -46.64 -22.8 -25 -26.13 -53.57 -74.51 T K 288 281.5 275 268.51 262.02 255.53 249.04 242.55 236.06 229.58 223.1 216.5 216.5 221.4 226.36 250.2 248 246.87 219.43 198.49 P kPa 101.3 89.88 79.5 70.12 61.66 54.05 47.22 41.11 35.65 30.8 26.5 12.11 5.529 2.549 1.197 0.287 0.0798 0.022 0.0052 0.0011 rho kg/m3 1.225 1.112 1.007 0.9093 0.8194 0.7364 0.6601 0.59 0.5258 0.4671 0.4135 0.1948 0.0889 0.0401 0.0184 0.004 0.001 0.0003 8E-05 2E-05 Consider an infinite flat plate of aircraft at 15° angle of attack in a Mach of 9 at an altitude of 60 km. Assume span length of 1 m. i. Sketch shock waves and expansion fan and streamline passing through the flat plate. (1 point) Also, draw the lift and drag forces on the plate. (1 point) Calculate the Mach number, temperature, density, pressure, total temperature, total pressure on top surface of plate. (1.5 point) Calculate the Mach number, temperature, density, pressure, total temperature, total pressure on the botttom surface of plate. (1.5 point) Calculate the lift and drag forces. (1 point) Calculate lift and drag coefficients. (1 point); Also, calculate the lift-to-drag ratio. (1 point) ii. iii. iv. V. vi. vii. h m 0 1000 2000 3000 4000 5000 6000 7000 8000 9000 10000 15000 20000 25000 30000 40000 50000 60000 70000 80000 km 0 1 2 3 4 LO 5 LO 6 7 8 10 15 20 25 30 40 50 60 70 80 T C 15 8.5 2 -4.49 -10.98 -17.47 -23.96 -30.45 -36.94 -43.42 -49.9 -56.5 -56.5 -51.6 -46.64 -22.8 -25 -26.13 -53.57 -74.51 T K 288 281.5 275 268.51 262.02 255.53 249.04 242.55 236.06 229.58 223.1 216.5 216.5 221.4 226.36 250.2 248 246.87 219.43 198.49 P kPa 101.3 89.88 79.5 70.12 61.66 54.05 47.22 41.11 35.65 30.8 26.5 12.11 5.529 2.549 1.197 0.287 0.0798 0.022 0.0052 0.0011 rho kg/m3 1.225 1.112 1.007 0.9093 0.8194 0.7364 0.6601 0.59 0.5258 0.4671 0.4135 0.1948 0.0889 0.0401 0.0184 0.004 0.001 0.0003 8E-05 2E-05