Aerospace Engineering Gate Yearwise 


Aerospace Engineering GATE 2018 Questions with Answer

Ques 1 Aerodynamics

A NACA 0012 airfoil has a trailing edge flap. The airfoil is operating at an angle of attack of 5 degrees with un-deflected flap. If the flap is now deflected by 5 degrees downwards, the CL versus α curve

A

shifts right and slope increases.

B

shifts left and slope increases.

C

shifts left and slope stays the same.

D

shifts right and slope stays the same.


Ques 2 Aerodynamics

The velocity profile in an incompressible, laminar boundary layer is shown in the figure below. U is the free-stream velocity, u(y) is the stream-wise velocity component. The area of the black shaded region in the figure below represents the

A

boundary layer thickness.

B

momentum thickness.

C

displacement thickness.

D

shape factor.


Ques 3 Aerodynamics

The pitching moment of a positively cambered NACA airfoil about its leading edge at zero-lift angle of attack is

A

negative.

B

positive.

C

indeterminate.

D

zero.


Ques 4 Aerodynamics

In a low-speed wind tunnel, the angular location(s) from the front stagnation point on a circular cylinder where the static pressure equals the free-stream static pressure, is

A

±380

B

±300

C

±600

D

00


Ques 5 Aerodynamics

A thermocouple, mounted flush in an insulated flat surface in a supersonic laminar flow of air measures the

A

static temperature.

B

temperature greater than static but less than total temperature.

C

total temperature.

D

temperature greater than total temperature.


Ques 6 Aerodynamics

A shock wave is moving into still air in a shock tube. Which one of the following happens to the air?

A

static temperature increases, total temperature remains constant.

B

static temperature increases, total temperature increases.

C

static temperature increases, total temperature decreases.

D

static pressure increases, total temperature remains constant.


Ques 7 Aerodynamics

A thin airfoil is mounted in a low-speed, subsonic wind tunnel, in which the Mach number is 0.1. At a point on the airfoil, the pressure coefficient is measured to be -1.2. If the flow velocity is increased such that the free-stream Mach number is 0.6, the pressure coefficient at the same point on the airfoil will approximately be:

A

-3.5

B

-2.9

C

-1.5

D

-0.75


Ques 8 Aerodynamics

Consider a 20° half-angle wedge in a supersonic flow at Mach 3.0 at standard sea-level conditions. If the shock-wave angle on the wedge is 36°, the Mach number of the tangential component of the flow post-shock is ________ (accurate to two decimal places).


Ques 9 Aerodynamics

The boundary layer thickness at the location of a sensor on a flat plate in an incompressible, laminar flow of air is required to be restricted to 1 mm for an effective measurement. If the flow velocity is 20 m/s with 1 bar pressure, 300 K temperature, and 1.789×10−5 kg/(m-s) viscosity, the maximum distance (in mm) of the sensor location from the leading edge is ________ (accurate to one decimal place).


Ques 10 Engineering Mathematics

Let →a →b be two distinct vectors that are not parallel. The vector →c=→a×→b

A

zero.

B

orthogonal to →a alone.

C

orthogonal to →a+→b.

D

orthogonal to →b alone.


Ques 11 Engineering Mathematics

Consider the function f(x,y)=x2/2+y2/3−5 All the roots of this function

A

form a finite set of points.

B

lie on an elliptical curve.

C

lie on the surface of a sphere.

D

lie on a hyperbolic curve.


Ques 12 Engineering Mathematics

Consider a vector field given by xî+yj+zk. This vector field is

A

divergence-free and curl-free.

B

curl-free but not divergence-free.

C

divergence-free but not curl-free.

D

neither divergence-free nor curl-free.


Ques 13 Engineering Mathematics

The determinant of the matrix is ________(accurate to one decimal place).


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