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SATHYABAMA UNIVERSITY
(Established under section 3 of UGC Act,1956)
Course & Branch :B.E - AERO
Title of the Paper :Aircraft Performance Max. Marks:80
Sub. Code :SAEX1012(2010) Time : 3 Hours
Date :16/04/2013 Session :AN
PART - A (10 x 2 = 20)
Answer ALL the Questions
1. Explain why induced drag of a finite wing is more than that of an
2. What is the effect of Reynolds number on skin friction drag?
3. Plot the variation of Thrust required with flight velocity in steady
level flight and give a brief explanation.
4. Explain the terms Absolute Ceiling and Service Ceiling?
5. What is the mean by dihedral effect?
6. What is mean by Wing twist and what is its importance?
7. What are all the advantages of keeping sweepback?
8. Draw a neat sketch of Drag Polar curve.
9. Explain the significance of 'load factor’?
10. Why propeller blades are given geometric twist from root to tip?
PART – B (5 x 12 = 60)
Answer ALL the Questions
11. 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.
(or)
12. Derive the expression for drag polar and explain it with a neat sketch
13. (a) Discuss some methods of thrust augmentation.
(b) Write a brief note on Drag reduction of Airplane.
(or)
14. (a) Explain briefly what is thrust reversal.
(b) Draw the power required and power available curve for a jet engine and piston engine and state your observations.
(c) Write a brief note on Airfoil characteristics.
15. Write short notes on:
(a) Glide Hodograph (b) V- η Diagram
(or)
16. Show that for steep angles of climb θ, P/Po = (1+ tan θ) cos3/2 θ Where P is thrust power used for climb and Po is the power required for steady level flight at same incidence and altitude.
17. Obtain the expression for turn radius and turn rate for pull up and pushover maneuver.
(or)
18. (a) Derive the Brequette Range formula for Jet-Propelled airplanes. (8)
(b) Write a brief note on high lift devices. (4)
19. (a) Define Take off distance and derive a suitable formula for estimating the same. (8)
(b) Discuss the factors affecting the endurance of a Propeller-driven airplane. (4)
(or)
20. An airscrew is required to produce a thrust of 4000N at a flight speed of 120 m/s at sea level. If the diameter is 2.5 m, estimate the minimum power which must be supplied based on Froude’s Momentum theory of Propulsion.
