Aerospace Engineering Gate Yearwise 


Aerospace Engineering GATE 2012 Questions with Answer

Ques 1 Aerodynamics

Bernoulli's equation is valid under steady state

A

only along a streamline in inviscid flow, and between any two points in potential flow.

B

between any two points in both inviscid flow and potential flow.

C

between any two points in inviscid flow, and only along a streamline in potential flow.

D

only along a streamline in both inviscid flow and potential flow.


Ques 2 Aerodynamics

An airfoil generates a lift of 80 N when operating in a freestream flow of 60 m/s. If the ambient pressure and temperature are 100 kPa and 290 K respectively (specific gas constant is 287 J/kg-K). the circulation on the airfoil in m2/s is


Ques 3 Aerodynamics

An oblique shock wave with a wave angle β is generated from a wedge angle of θ. The ratio of the Mach number downstream of the shock to its normal component is

A

sin(β-θ)

B

cos(β-θ)

C

sin(θ-β)

D

cos(θ-β)


Ques 4 Aerodynamics

In a closed-circuit supersonic wind tunnel, the convergent-divergent (C-D) nozzle and test section are followed by a C-D diffuser to swallow the starting shock. Here, we should have the

A

diffuser throat larger than the nozzle throat and the shock located just at the diffuser throat.

B

diffuser throat larger than the nozzle throat and the shock located downstream of the diffuser throat.

C

diffuser throat of the same size as the nozzle throat and the shock located just at the diffuser throat.

D

diffuser throat of the same size as the nozzle throat and the shock located downstream of the diffuser throat.


Ques 5 Aerodynamics

A vortex flowmeter works on the principle that the Strouhal number of 0.2 is a constant over a wide range of flow rates. If the bluff-body diameter in the flowmeter is 20 mm and the piezo-electric transducer registers the vortex shedding frequency to be 10 Hz, then the velocity of the flow would be measured as

A

0.1 m/s

B

1 m/s

C

10 m/s

D

100 m/s


Ques 6 Aerodynamics

For a symmetric airfoil, the lift coefficient for zero degree angle of attack is

A

-1.0

B

0.0

C

0.5

D

1.0


Ques 7 Aerodynamics

The critical Mach number of an airfoil is attained when

A

the freestream Mach number is sonic.

B

the freestream Mach number is supersonic.

C

the Mach number somewhere on the airfoil is unity.

D

the Mach number everywhere on the airfoil is supersonic.


Ques 8 Aerodynamics

The shadowgraph flow visualization technique depends on

A

the variation of the value of density in the flow.

B

the first derivative of density with respect to spatial coordinate.

C

the second derivative of density with respect to spatial coordinate.

D

the third derivative of density with respect to spatial coordinate.


Ques 9 Aerodynamics

The Mach angle for a flow at Mach 2.0 is

A

30°

B

45°

C

60°

D

90°


Ques 10 Aerodynamics

For a wing of aspect ratio AR, having an elliptical lift distribution, the induced drag coefficient is (where CL is the lift coefficient)

A

CL/(πAR)

B

CL2/(πAR)

C

CL/(2πAR)

D

CL2/(πAR2)


Ques 11 Aerospace Propulsion

The ratio of flight speed to the exhaust velocity for maximum propulsion efficiency is

A

0.0

B

0.5

C

1.0

D

2.0


Ques 12 Aerospace Propulsion

The ideal static pressure coefficient of a diffuser with an area ratio of 2.0 is

A

0.25

B

0.50

C

0.75

D

1.0


Ques 13 Aerospace Propulsion

A rocket motor has combustion chamber temperature of 2600 K and the products have molecular weight of 25 g/mol and ratio of specific heats 1.2. The universal gas constant is 8314 J/kg-mole-K. The value of theoretical c*(in m/s) is


Unique Visitor Count

Total Unique Visitors

Loading......