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Title of Report : AERO2562 - Assignment 2 2020 (2) Author: Microsoft Office User Save Date: 2020 Page 1 of 5 School of Engineering AERO2562 - Assignment 2- Aircraft Performance Total Marks: 165 2020 1 Question 1 (10 marks) Consider an airplane modelled after the twin-engine Beechcraft Queen Air executive transport. The airplane has the following characteristics: weight is 38,220 N; wing area is 27.3 m2; aspect ratio is 7.5; Oswald efficiency factor is 0.9; and zero-lift drag coefficient CD,0 is 0.03. 1.a. Calculate the thrust required to fly at a velocity of 725 km/h at standard sea level. Assume the value of ρ∞ = 1.225 kg/m3 at standard sea level. (Round the final answer to the nearest whole number.) 1.b. Calculate the thrust required to fly with a velocity of 675 km/h at an altitude of 4.5 km. Assume the value of ρ∞ = 0.777 kg/m3at an altitude of 4.5 km. (Round the final answer to the nearest whole number.) 1.c Calculate and graph the maximum velocity of the Beechcraft Queen Air with respect to altitude. Construct the graph between sea level and a maximum altitude of 20,000 ft. 2 Question 2 (10 marks) 2. An airplane weighing 5,000 lb is flying at standard sea level with a velocity of 700 km/h. At this velocity, the L/D ratio is a maximum. The wing area and aspect ratio are 200 ft2 and 8.5, respectively. The Oswald efficiency factor is 0.93. Calculate the total drag on the airplane. Assume ρ∞ = 0.002377 slug/ft3. (Round the final answer to one decimal place.) School/Department/Area : AERO2562 - Assignment 2 2020 (2) Author: Microsoft Office User Save Date: 28/04/2020 Page 2 of 5 3 Question 3 (15 marks) Consider an airplane modelled after the Fairchild Republic A-10, a twin-jet attack aircraft. The airplane has the following characteristics: wing area = 47 m2; aspect ratio = 6.5; Oswald efficiency factor = 0.87; weight = 103,047 N; and zero-lift drag coefficient = 0.032. The airplane is equipped with two jet engines, each with 40,298 N of static thrust at sea level. Assume the velocity of the airplane is 160 m/s. 3.a. Calculate the power required at sea level. (Round the final answer to the nearest whole number. Answer this part of the question before moving on to the next part.) 3.b. Calculate the maximum velocity at sea level. (Round the final answer to the nearest whole number. Answer this part of the question before moving on to the next part.) 3.c. Calculate the velocity, Valt, power, Palt, required at 5 km altitude. Assume ρ at 5 km altitude = 0.7364 kg/m3. (Round the final answers to the nearest whole number. Answer this part of the question before moving on to the next part.) 3.d. Calculate the maximum velocity at 5 km altitude. Assume ρ at 5 km altitude = 0.7364 kg/m3. (Round the final answer to the nearest whole number.) 4 Question 4 (15 marks) Consider a model of a wing–body shape mounted in a wind tunnel. The flow conditions in the test section are standard sea-level properties with a velocity of 140 m/s. The wing area and chord are 1.5 m2 and 0.45 m, respectively. Using the wind tunnel force and moment-measuring balance, the moment about the center of gravity when the lift is zero is found to be −12.4N.m. When the model is pitched to another angle of attack, the lift and moment about the center of gravity are measured to be 3675 N and 20.67N.m, respectively. Calculate the value of the moment coefficient about the aerodynamic center and the location of the aerodynamic center. (Round the final answers to three decimal places.) 5 Question 5 (15 marks) 5. Consider a model of a wing–body shape mounted in a wind tunnel. The flow conditions in the test section are standard sea-level properties with a velocity of 100 m/s. The wing area and chord are 1.5 m2 and 0.45 m, respectively. Using the wind tunnel force and moment-measuring balance, the moment about the center of gravity when the lift is zero is found to be −12.4 N.m. When the model is pitched to another angle of attack, the lift and moment about the center of gravity are measured to be 3675 N and 20.67 N.m, respectively. Assume that a horizontal tail with no elevator is added to this model. The distance from the airplane’s center of gravity to the tail’s aerodynamic center is 1.0 m. The area of the tail is 0.4 m2, and the tail setting angle is 2.0°. The lift slope of the tail is 0.12 per degree. From experimental measurement, ε0 = 0 and ∂ε / ∂α = 0.46. If the absolute angle of attack of the model is 5° and the lift at this angle of attack is 4134 N, calculate the moment about the center of gravity. (Round the final answer to the nearest whole number.) School/Department/Area : AERO2562 - Assignment 2 2020 (2) Author: Microsoft Office User Save Date: 28/04/2020 Page 3 of 5 6 Question 6 (15 marks) 6. A finite wing area of 0.14 m^2 and aspect ratio of 6 is tested in a subsonic wind tunnel at a velocity of 57.9 m/s at standard sea-level conditions. At an angle of attack of −1°, the measured lift and drag are 0 and 0.81 N, respectively. At an angle of attack of 2°, the lift and drag are measured as 22.2 and 1.02 N, respectively. Calculate the span efficiency factor and the finite- wing lift slope. (Round the final answers to three decimal places.) 7 Question 7 (15 marks) Consider a finite wing with an aspect of ratio of 7. The airfoil section of the wing is a symmetric airfoil with an infinite-wing lift slope of 0.11 per degree. The lift-to-drag ratio for this wing is 21 when the lift coefficient is equal to 0.57. If the angle of attack remains the same and the aspect ratio is simply increased to 10 by adding extensions to the span of the wing, what is the new value of the lift-to-drag ratio? Assume span efficiency factor where e = e1 = 0.9 for both cases. (Round the final answer to one decimal place.) 8 Question 8 (20 marks) Consider a NACA 2412 airfoil in a low-speed flow at zero degrees angle of attack and a Reynolds number of 8.9 ×10^6. Estimate the percentage of drag from pressure drag due to flow separation (form drag). Assume a fully turbulent boundary layer over the airfoil. For NACA 2412 at zero degrees angle of attack, Cd = 0.008. 9 Question 9 (20 marks) 9. The wing of the Fairchild Republic A-10A twin-jet close-support airplane is approximately rectangular with a wingspan (the length perpendicular to the flow direction) of 17.5 m and a chord (the length parallel to the flow direction) of 3 m. The airplane is flying at standard sea level with a velocity of 200 m/s. Assume the wing is approximated by a flat plate and incompressible flow. If the critical Reynolds number for transition is 106, calculate the skin friction drag for the wing. Use turbulent drag as 2830 N. (Round the final answer to the nearest whole number.) 10 Question 10 (30 marks) 10.a Describe in detail the way in which a Jet engine produces thrust. In your description you may use equations, diagrams and graphs to explain and clarify your answer. 10.b Describe in detail the way in which a Turbofan engine produces thrust. In your description you may use equations, diagrams and graphs to explain and clarify your answer. 10.c Describe in detail the way in which a Piston engine produces thrust. In your description you may use equations, diagrams and graphs to explain and clarify your answer. School/Department/Area : AERO2562 - Assignment 2 2020 (2) Author: Microsoft Office User Save Date: 28/04/2020 Page 4 of 5 School/Department/Area : AERO2562 - Assignment 2 2020 (2) Author: Microsoft Office User Save Date: 28/04/2020 Page 5 of 5 APPENDIX A