Register Number
SATHYABAMA UNIVERSITY
(Established under section 3 of UGC Act,1956)
Course & Branch :B.E - AERO
Title of the Paper :Aircraft Performance
Sub. Code :SAEX1012 (2010)
Date :07/11/2012
Max. Marks:80
Time : 3 Hours
Session :FN
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1.
PART - A
(10 x 2 = 20)
Answer ALL the Questions
Distinguish between troposphere and stratosphere.
2.
Define pressure altitude, density altitude and temperature
altitude.
3.
Write the expression for shaft power.
4.
Write the expression for thrust developed in an air breathing
engine. How does it differ from a non air breathing engine?
5.
What are the conditions required for minimum drag and
minimum power?
6.
Write the expression for endurance for jet propelled airplanes.
7.
Write the expression for pull up and pull down maneuvers.
8.
How the landing performances of an airplane can be reduced?
9.
Draw a typical variation of drag polar.
10. What do you mean by relative velocity?
PART – B
(5 x 12 = 60)
Answer All the Questions
11. Derive an expression for variation of density and pressure in the
STRATOSPHERE region.
(or)
12. An airplane is with the wing area of 206 m2, an aspect ratio of 10,
Cd=0.006 and a span effectiveness factor of 0.95. The weight of
the airplane is 7.5 x 105 N. At an altitude of 3 km and flight
velocity of 100 m/s, calculate the total drag on the airplane.
13. Explain and show the variation of thrust and TSFC with
supersonic Mach number for a turbojet engine.
(or)
14. Show the variation of pressure, temperature, velocity and thrust
through a turbojet engine.
15. Calculate range and endurance for a jet powered aircraft and
state the condition for maximum range and endurance.
(or)
16. The overall drag coefficient (based on wing area “S”) of a
particular aircraft of weight “w” is given by Cd = a+b CL2, where
a and b are constants derive expression for
(a) Minimum drag in horizontal flight.
(b)Magnitude of the dynamic pressure at which this occurs.
(c) The corresponding power required.
17. Obtain the expression for turn radius and turn rate for pull up and
pushover maneuver.
(or)
18. Show that - Ground effect, φ= [16(h/b) 2]/ [1+16(h/b) 2].
19. A high speed subsonic aircraft is flying at a pressure altitude of
10 km. A pitot tube on the wing tip measures a pressure of 4.24 x
104 N/m2. Calculate the Mach number at which the airplane is
flying. If the ambient air temperature is 230K. Calculate the true
airspeed and calibrated air speed.
(or)
20. Calculate the dynamic pressure of a flow with V∞ =200 m/s, P∞ =
1 atm, and T∞ = 300K.what will be the percentage of error if the
flow is treated as incompressible?