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Aerospace Engineering GATE 2017 Questions with Answer

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Ques 1 Aerodynamics

Consider a straight wing with rectangular planform of aspect ratio 10 and with a NACA 0012 airfoil. The span effectiveness factor for this wing is 0.95. Assume the flow to be incompressible and governed by thin airfoil theory. The lift coefficient of this wing, at an angle of attack of 6 deg, is _______ (in three decimal places).

0.540 to 0.550 is the correct answer.

Ques 2 Aerodynamics

Consider an incompressible flow over a flat plate with the following approximation to the velocity profile:

where δ is the boundary layer thickness and U the free-stream speed. The normalized momentum thickness (θ/δ) for this profile is _______ (in three decimal places).

0.165 to 0.168 is the correct answer.

Ques 3 Aerospace Engineering

Which one of the following statements is NOT true

The pitching moment of any airfoil at any angle of attack is always zero at the center of pressure

The pitching moment of any airfoil at any angle of attack is always zero at the aerodynamic center

The center of pressure and aerodynamic center coincide for a symmetric airfoil

The pitching moment about the aerodynamic center, for any airfoil, does not vary with angle of attack

Ques 4 Aerospace Engineering

Which one of the following statements is NOT true

Compared to a laminar boundary layer, a turbulent boundary layer is more desirable on a wing operating at large angle of attack

The skin friction drag for a turbulent boundary layer is larger than that for a laminar boundary layer

The location of transition from laminar to turbulent boundary layer depends only on the operating Reynolds number

A separated flow does not necessarily lead to a turbulent boundary layer

Ques 5 Aerospace Engineering

A De Laval nozzle is to be designed for an exit Mach number of 1.5. The reservoir conditions are given as P_∘=1 atm (gage), T_∘=20°C. γ=1.4. Assuming shock free flow in the nozzle, the exit absolute pressure (in atm) is (in three decimal places)

0.540 is the correct answer.

Ques 6 Aerospace Engineering

Consider a steady one dimensional flow of a perfect gas with heat transfer in a duct. The T-s diagram (shown below) shows both the static and the stagnation conditions at two locations. A and B, in the duct. A_t and B_t denote stagnation conditions for states A and B, respectively. It is known that (ΔT)_A = (ΔT)_B. M_A and M_B are the Mach numbers of the flow at locations A and B.

Which of the following statements is true about the flow.

Flow is subsonic and M_A < M_B.

Flow is supersonic and M_A > M_B

Flow is subsonic and M_A > M_B

Flow is supersonic and M_A < M_B

Ques 7 Aerospace Engineering

To ensure only the longitudinal static stability (and not the condition for equilibrium) of a low speed aircraft, the aircraft components must be designed to satisfy which one of the following conditions:

∂c_m/∂α < 0

∂C_m/∂α < 0

∂õc_m/∂c_L < 0 and C_m0 > 0

∂C_m/∂c_L = 0.0 and C_m0 < 0

Ques 8 Aerospace Engineering

Which of the following statement(s) is / are true about the shear centre of a cross-section:
P: It is that point in the cross-section through which shear loads produce no twisting.
Q: This point is also the centre of twist of sections subjected to pure torsion.
R: The normal stress at this point is always zero.

P, Q and R

P only

P and Q only

P and R only

Ques 9 Aerospace Engineering

Let ―N_m and ―N₀ be respectively the non-dimensional locations of the stick-fixed maneuver point and stick-fixed neutral point of a low speed conventional aircraft. These distances are measured with respect to the nose of the fuselage. The numerical value of ―N_m - ―N₀

will always be negative

will always be positive

will always be zero

can have any value depending on the location of the center of gravity of the aircraft

Ques 10 Aerospace Engineering

The phenomenon of rudder lock in conventional low speed aircraft is primarily due to

large value of directional derivative. C_nβ

the sidewash due to fuselage on the vertical stabilizer

the tendency of rudder to float rapidly at high angles of side-slip

the sidewash due to wing on the vertical stabilizer

Ques 11 Aerospace Engineering

The period of revolution of earth about the sun is 365.256 days, approximately. The semi-major axis of the earth's orbit is close to 1.4953 × 10¹¹ m. The semi-major axis of the orbit of Mars is 2.2783 × 10¹¹ m. The period of revolution of Mars, about the sun, is Earth days (in three decimal place)

686.5 is the correct answer.

Ques 12 Aerospace Engineering

Consider a system consisting of certain amount of perfect gas enclosed in a cylinder fitted with a frictionless piston. This system can undergo following processes
(i) Expansion with finite pressure difference with the surrounding.
(ii) Compression with infinitesimal pressure difference with the surrounding.
(iii) Heat transfer with finite temperature difference with the reservoir.
(iv) Heat transfer with infinitesimal temperature difference with the reservoir.

Out of these which processes are reversible?

(i) and (iii)

(i) and (iv)

(ii) and (iii)

(ii) and (iv)

Ques 13 Aerospace Engineering

Among the following engines, which one is expected to have the maximum Specific Impulse?

Cryogenic Rocket

Solid Propellant Rocket

Liquid Propellant Rocket

SCRAM Jet

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