Aerospace Engineering GATE 2025 Questions with Answer

Ques 1 Aerodynamics

The lift per unit span for a spinning circular cylinder in a potential flow is 6 N/m. The free-stream velocity is 30 m/s, and the density of air is 1.225 kg/m³. The circulation around the cylinder is ______ m²/s (rounded off to two decimal places).

Ques 2 Aerodynamics

A lifting surface has a spanwise circulation distribution of Γ(θ)=A sin 3θ (where A≠0) over its span -b/2 ≤ y ≤ b/2, and y=-(b/2)cos θ is the spanwise coordinate.
Furthermore, the downwash varies along the span as ω(θ)=V_∞(3A sin 3θ / sin θ). where V_∞ is the freestream velocity.
Which one of the following options represents the total lift (L) and induced drag (D_i)?

Ques 3 Aerodynamics

An aircraft is flying at an altitude of 4500 m above sea level, where the ambient pressure, temperature and density are 57 kPa, 259 K and 0.777 kg/m³, respectively. The speed of the aircraft (V) is 230 m/s. Gas constant R=287 J/kg/K, and specific heat ratio γ=1.4. If the stagnation pressure is p_o, and static pressure is p, the value of (p_o-p)/(1/2 ρ V²) is ______ (rounded off to two decimal places).

Ques 4 Aerodynamics

A rectangular wing of 1.2 m chord length and aspect ratio 5 is tested in a wind tunnel at an air speed of 60 m/s. The density and the dynamic viscosity of air are 1.3 kg/m³ and 1.8×10^-5 kg/m-s, respectively. A second rectangular wing of the same span, but with an aspect ratio of 6, is to be tested in the same tunnel at the same Reynolds number. The air speed at which the second test should be performed is ______ m/s (answer in integer).

Ques 5 Aerodynamics

In a low-speed airplane, a venturimeter with 1.3:1 area ratio is used for airspeed measurement. The airplane's maximum speed at sea level is 90 m/s. If the density of air at sea level is 1.225 kg/m³ the maximum pressure difference between the inlet and the throat of the venturimeter is ______ kPa (rounded off to two decimal places).

Ques 6 Aerodynamics

A supersonic stream of an ideal gas at Mach number M₁=5 is turned by a ramp, as shown in the figure. The ramp angle is 20°. The pressure ratio is p₂/p₁=7.125 and the specific heat ratio is γ=1.4. The pressure coefficient on the ramp surface is ______ (rounded off to two decimal places).

Ques 7 Aerodynamics

The mass flow rate in a supersonic wind tunnel is 2 kg/s when the stagnation pressure and stagnation temperature are 1 MPa and 800 K, respectively. If the stagnation pressure and stagnation temperature are changed to 3 MPa and 200 K, the mass flow rate in the tunnel changes to ______ kg/s (answer in integer).

Ques 8 Aerodynamics

For a two-dimensional incompressible flow over a flat plate, the laminar boundary layer thickness at a distance x from the leading edge is δ. If Re_x is the Reynolds number defined based on length scale x, (δ/x) is proportional to

Ques 9 Aerodynamics

For a NACA 4415 airfoil, the location of maximum camber, as a fraction of the chord length from the leading edge, is

Ques 10 Aerodynamics

A positively cambered airfoil is placed in a uniform flow (velocity, U_∞) at its zero-lift angle of attack. M is the corresponding pitching moment. Which one of the following representations accurately describes this scenario?

A

B

C

D

Ques 11 Aerodynamics

Consider a pair of point vortices with clockwise circulation Γ each. The distance between their centers is a, as shown in the figure. Assume two-dimensional, incompressible, inviscid flow. Which one of the following options is correct?

Ques 12 Aerodynamics

In a fluid flow, Mach number is an estimate of

Ques 13 Engineering Mathematics

The maximum value of the function f(x)=(x-1)(x-2)(x-3) in the domain [0, 3] occurs at x = ______ (rounded off to two decimal places).