Aerospace Engineering Gate Yearwise 


Aerospace Engineering GATE 2023 Questions with Answer

Ques 14 Aircraft Propulsion

Consider a cryogenic liquid rocket engine using an expander cycle with liquid hydrogen and liquid oxygen as the two propellants. The mass flow rate of hydrogen ṁH2 into the combustion chamber is 32 kg/s, and the mass flow rate of oxygen ṁO2 into the chamber is such that ṁO2/ṁH2 = 8. The combustion of hydrogen and oxygen is at stoichiometry. Assuming that the rate of the forward reaction is much larger than that of the reverse reaction, the rate of formation of H2O is _______ kmol/s. (round off to the nearest integer)

1 is the correct answer.


Ques 15 Aircraft Structures

Which of the following statement(s) is/are true about the ribs of an airplane wing with semi-monocoque construction?

A

For a rectangular planform wing, the dimensions of the ribs DO NOT depend on their spanwise position in the wing.

B

Ribs increase the column buckling stress of longitudinal stiffeners connected to them.

C

Ribs increase plate buckling stress of the skin panels.

D

Ribs help in maintaining the aerodynamic shape of the wing.


Ques 16 Aircraft Structures

Which of the following statement(s) about the elastic flexural buckling load of columns is/are correct?

A

The buckling load increases with an increase in flexural rigidity of the column.

B

The buckling load increases with an increase in the length of the column.

C

The boundary conditions of the column affect the buckling load.

D

The buckling load is NOT directly dependent on the density of the material used for the column.


Ques 17 Aircraft Structures

The shear flow distribution in a single cell, thin-walled beam under the action of an arbitrary shear load sy applied at the shear center S is shown in the figure. The cell has horizontal symmetry with booms marked by 1 to 4 that carry direct stresses. The shear modulus G is the same for all the walls, and the area of the cell is 135000 mm2. With respect to the point O marked in the figure, the distance to the shear center S is _______ mm. (round off to the nearest integer)

a is the correct answer.


Ques 18 Calculus

The direction in which a scalar field φ(x, y, z) has the largest rate of change at any point with position vector r⃗ = xî + yĵ + zk̂ is the same as that of the vector

A

∇φ

B

∇ x (φr⃗)

C

φr⃗

D

(∇φ • dr⃗)r⃗


Ques 19 Calculus

If a monotonic and continuous function y = f(x) has only one root in the interval x1 < x < x2, then

A

f(x1)f(x2) > 0

B

f(x1)f(x2) = 0

C

f(x1)f(x2) < 0

D

f(x1) - f(x2) = 0


Ques 20 Differential Equations

Consider the one-dimensional wave equation ∂u/∂t + ∂u/∂x = 0 for -∞ < x < ∞, t ≥ 0. For an initial condition u(x, 0) = e-x2, the solution at t = 1 is

A

u(x, 1) = e-(x-1)2

B

u(x, 1) = e-1

C

u(x, 1) = e-x2

D

u(x, 1) = e-(x+1)2


Ques 21 Differential Equations

Consider the equation dy/dx + ay = sin(ωx), where a and ω are constants. Given y = 1 at x = 0, select all correct statement(s) from the following as x → ∞.

A

y → 0 if a ≠ 0

B

y → 1 if a = 0

C

y → A exp(|a|x) if a < 0; A is a constant

D

y → B sin(ωx + C) if a > 0; B and C are constants


Ques 22 Flight Mechanics

An ideal glider has drag characteristics given by CD = CD0 + CDi, where CDi = KCL2 is the induced drag coefficient, CL is the lift coefficient, and K is a constant. For maximum range of the glider, the ratio CD0/CDi is

A

1

B

1/3

C

3

D

3/2


Ques 23 Flight Mechanics

For a longitudinally statically stable aircraft, which one of the following represents the relationship between the coefficient of pitching moment about the center of gravity Cmcg and absolute angle of attack αa? (Note: nose-up moment is positive.)

A

B

C

D


Ques 24 Flight Mechanics

Consider the four basic symmetrical flight loading conditions corresponding to the corners of a typical V-n diagram. For one of these flight loading conditions, it is observed that (i) the compressive bending stresses have a maximum value in the bottom aft region (see figure) of the wing cross-section; and (ii) the tensile bending stresses are maximum in the upper forward region (see figure) of the wing cross-section. For the preceding observations, select the corresponding flight loading condition from the options given.

A

Positive high angle of attack

B

Positive low angle of attack

C

Negative high angle of attack

D

Negative low angle of attack


Ques 25 Flight Mechanics

An airplane weighing 40 kN is landing on a horizontal runway during which it is retarded by an arresting cable mechanism. The tension in the arresting cable at a given instant, as shown in the figure, is 100 kN. Assuming that the thrust from the engine continues to balance airplane drag, the magnitude of the horizontal load factor is _______. (round off to one decimal place)

1 is the correct answer.


Ques 26 Flight Mechanics

Airplane A and Airplane B are cruising at altitudes of 2 km and 4 km, respectively. The free stream density and static pressure at altitude 2 km are 1.01 kg/m3 and 79.50 kPa, respectively, and at altitude 4 km, they are 0.82 kg/m3 and 61.70 kPa, respectively. The differential pressure reading from the pitot-static tubes is 3 kPa for both the airplanes. Assuming incompressible flow, the ratio of cruise speeds of Airplane A to Airplane B is _______. (round off to two decimal places)

1 is the correct answer.


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