Aircraft Performance. Aeronautical Engineering

Topics: Aerodynamics, Propeller, Lift Pages: 3 (693 words) Published: August 24, 2013
MODEL QUESTION PAPER B.E. Aeronautical Engineering Semester : V AE333 - AIRCRAFT PERFORMANCE Time 3 Hours Answer all the questions PART- A (10 x 2 = 20 Marks) 1. For a bluff body skin friction drag is more than pressure drag. True/ false. Justify your answer. 2. Two identical airfoils are kept in identical flow conditions. The surface of one Airfoil is relatively more rough. This airfoil will have higher stalling angle than the other. True/ False. 3. 4. 5. Justify your answer. Maximum Marks : 100

Explain why induced drag of a finite wing is more than that of an infinite wing. What is the effect of Reynolds number on skin friction drag? Plot the variation of Thrust required with flight velocity in steady level flight and give a brief explanation.

6. 7. 8. 9. 10

Explain the terms Absolute Ceiling and Service Ceiling? Define the tem Specific Air Range? What is the role of spoilers during landing of an aircraft? Explain how load factor is related to the bank angle. Why propeller blades are given a geometric. Twist from root to tip? PART – B (5 x 16 = 80 Marks)


An aircraft is in steady level flight at sea level at speed of 100 m/s. The pilot causes his aircraft to enter a horizontal, correctly banked circle of l100 m radius keeping the same angle of incidence. The engine thrust is altered as necessary. Then the pilot brings the aircraft out of the turn without altering the angle of incidence and thrust and allows it to climb. Estimate the rate of climb, if at that incidence, the L/D ratio is 8.

12.a)i) An aircraft is flying at m times the speed corresponding to minimum drag in steady level flight. Show that,

1 D = 2 Dmin

(m2 + m-2)

Where D is the drag on the aircraft at the flight speed and D min is the minimum drag. (10) ii) Write a brief note on Drag reduction of Airplanes. OR 12.b)i) An aircraft is flying in steady level flight at η times its minimum power speed. 4 P 3  Show that = 4 where P is the power required at the flight...
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