GATE Aerospace Engineering online test paper 2
by Esha Upadhyay · Published · Updated
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Question 1 of 15
1. Question
A statically stable trimmed aircraft experiences a gust and the angle of attack reduces momentarily.As a result the center of pressure of the aircraft
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Question 2 of 15
2. Question
A ideal gas in a reservoir has a specific stagnation enthalpy of h.The gas is isentropically expanded to a new specific stagnation enthalpy of h/2 and velocity u.The flow is one dimensional and steady.Then u to the power 2 by h is equal to
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Question 3 of 15
3. Question
Isentropic efficencies of an aircraft engine operating at typical subsonic cruise conditions with the following components – intake,compressor,turbine and nozzle are denoted by I,C,T,N respectively.Which of the following is correct?
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Question 4 of 15
4. Question
A rocket nozzle is designed to produce maximum thrust at an altitude H = 8 KM from the sea level.The nozzle operates in
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Question 5 of 15
5. Question
A cube made of a linear elastic isotropic material is subjected to uniform hydrostatic pressure of 100 N per millimeter square.Under this load the volume of cube shrinks by .05%.The Young’s modulus for the material E = 300GPa.The poissons ratio of the material is
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Question 6 of 15
6. Question
For a thin plate at 2 degrees angle of attack the pitching moment coefficient about the trailing edge is
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Question 7 of 15
7. Question
A satellite is to be transferred from its geostationary orbit to a circular polar orbit of the same radius through a single impulse out of plane maneuver.The magnitude of the change in velocity required is ______________times the magnitude of escape velocity
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Question 8 of 15
8. Question
Air enters an Aircraft engine at a velocity of 180m/s with a flow rate of 94 kg/s.The engine combustor requires 9.2Kg/s of air to burn 1kg/s of fuel.The velocity of gas exiting from the engine is 640 m/s.The momentum thrust in N developed by the engine is
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Question 9 of 15
9. Question
A solid rocket motor is designed with a cylindrical end burning propellant grain of length 1m and diameter 32cm.The density of the propellant grain is 1750 kg per meter cube.The specific impulse of the motor is 190 s and the acceleration due to gravity is 9.8 m per sec square.If the propellant burns for a period of 150s then the thrust in N produced by the rocket motor is
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Question 10 of 15
10. Question
If all the eigen values of a matrix are real and equal then
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Question 11 of 15
11. Question
Determine the correctness or otherwise of the assertion and reason
Assertion(a): Aircraft directional static stability can be improved by moving the vertical tail rearward.
Reason(r): Moving the vertical tail rearward increases the moment arm from the tail aerodynamic center to aircraft center of gravity.Correct
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Question 12 of 15
12. Question
Following are the operational parameters of an axial compressor stage
Air mass flow rate : 24 kg/s
static temperature of air at rotor inlet : 278K
velocity of air at rotor inlet (zero whirl velocity) : 140 m/s
work done on the compressor rotor : 734 KJ
Isentropic efficiency of the compressor stage: .86
Ratio of specific heats : 1.4
specific heat at constant pressure: 1.005 KJ/KgKThe stagnation pressure ratio across the axial compressor stage is _________________”
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Question 13 of 15
13. Question
A 200mm long simply supported column has a 5mm * 10mm rectangular cross section. The Youngs modulus of the material is 200GPa.Assuming a factor of safety as 2.5 corresponding to the buckling load the maximum load in N the column can support in compression is (find the nearest ans)
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Question 14 of 15
14. Question
Hot gas (ratio of specific heats is 1.33) at the temperature of 1450K enters into an axial turbine and expands isentropically.Assume that kinetic energy of the gas across the turbine is negligible.If the ratio of inlet to outlet pressure of the turbine is 9.5 then the temperature in K of gas exiting the turbine is (choose nearest ans)
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Question 15 of 15
15. Question
For a real symmetric matrix [A], which of the following statements is true
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