Aerospace Engineering Gate Yearwise 


Aerospace Engineering GATE 2009 Questions with Answer

Ques 1 Aerodynamics

For a flow through a Prandtl-Meyer expansion wave

A

Mach number stays constant.

B

Entropy stays constant.

C

Temperature stays constant.

D

Density stays constant.


Ques 2 Aerodynamics

For two-dimensional irrotational and incompressible flows

A

Both potential and stream functions satisfy the Laplace equation.

B

Potential function must satisfy the Laplace equation but the stream function need not.

C

Stream function must satisfy the Laplace equation but the potential function need not.

D

Neither the stream function nor the potential function need to satisfy the Laplace equation.


Ques 3 Aerodynamics

A trailing edge plain flap deflected downward increases the lift coefficient of an airfoil by

A

Increasing the effective camber of the airfoil.

B

Delaying the separation of the flow from the airfoil surface.

C

Increasing the local airspeed near the trailing edge.

D

Controlling the growth of the boundary layer thickness along the airfoil surface.


Ques 4 Aerodynamics

Thin airfoil theory predicts that the lift slope is
dcldα=2π for

A

Symmetric airfoils only.

B

Cambered airfoils only.

C

Any airfoil shape.

D

Joukowski airfoils only.


Ques 5 Aerodynamics

An aircraft is flying at M=2 where the ambient temperature around the aircraft is 250 K. If the
specific heat ratio for air γ=1.4, the stagnation temperature on the surface of the aircraft is

A

200 K

B

450 K

C

350 K

D

1450 K


Ques 6 Aerodynamics

Which of the following statements are true for flow across a stationary normal shock ?
P. Stagnation temperature stays constant.
Q. Stagnation pressure decreases.
R. Entropy increases.
S. Stagnation pressure increases.
T. Stagnation temperature increases.

A

P, Q, R

B

Q, R, S

C

R, S, T

D

S, T, P


Ques 7 Aerodynamics

A model airfoil in a wind tunnel that is operating at 50 m/s develops a minimum pressure co-efficient
of-6.29 at some point on its upper surface. The local airspeed at that point is

A

50 m/s

B

125 m/s

C

135 m/s

D

150 m/s


Ques 8 Aerodynamics

A symmetrical airfoil section produces a lift coefficient of 0.53 at an angle of attack of 5 degrees
measured from its chord line. An untwisted wing of elliptical planform and aspect ratio 6 is made of
this airfoil. At an angle of attack of 5 degrees relative to its chordal plane, this wing would produce a
lift coefficient of

A

0.53

B

0.48

C

0.40

D

0.36


Ques 9 Aircraft Systems

A conventional altimeter is a

A

Pressure transducer

B

Temperature transducer

C

Density transducer

D

Velocity transducer


Ques 10 Engineering Mathematics

The ordinary differential equation
d2ydx2+ky=0 where k is real and positive

A

is non-linear

B

has a characteristic equation with one real and one complex root

C

has a characteristic equation with two real roots

D

has a complementary function that is simple harmonic


Ques 11 Engineering Mathematics

A non-trivial solution to the (n×n) system of equations
[A]{x}={0}, where {0} is the null vector

A

can never be found

B

may be found only if [A] is not singular

C

may be found only if [A] is an orthogonal matrix

D

may be found only if [A] has at least one eigenvalue equal to zero


Ques 12 Engineering Mathematics

The value of the integral ∫π0dx/1+x+sin x evaluated using the trapezoidal rule with two equal intervals is
approximately

A

1.27

B

1.81

C

1.41

D

0.71


Ques 13 Engineering Mathematics

The product of the eigenvalues of the matrix is

A

20

B

24

C

9

D

17


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