Aerospace Engineering GATE 2024 Questions with Answer

Ques 1 Aerodynamics

Which one of the following figures represents the drag polar of a general aviation aircraft?

A

B

C

D

Ques 2 Aerodynamics

Using thin airfoil theory, the lift coefficient of a NACA 0012 airfoil placed at 5° angle of attack in a uniform flow is _______ (rounded off to 2 decimal places).

Ques 3 Aerodynamics

As per the International Standard Atmosphere model, which one of the following options about density variation with increase in altitude in the isothermal layer is correct?

Ques 4 Aerodynamics

The figure (not to scale) shows a control volume to estimate the forces on the airfoil with elliptic cross-section. Surfaces 2 and 3 are streamlines. Velocity profiles are measured at the upstream end (surface 1) and at the downstream end (surface 4) of the control volume. The drag coefficient for the airfoil is defined as C_d = D/(1/2 * ρ * U_∞² * c), where D is the drag force on the airfoil per unit span and ρ is the density of the air. The static pressure, p_∞, is constant over the entire surface of the control volume. Assuming the flow to be incompressible, two-dimensional, and steady, the C_d for the airfoil is _______ (rounded off to 3 decimal places).

Ques 5 Aerodynamics

It is desired to estimate the aerodynamic drag, D, on a car traveling at a speed of 30 m/s. A one-third scale model of the car is tested in a wind tunnel following the principles of dynamic similarity. The drag on the scaled model is measured to be D_m. The ratio D/D_m is _______ (rounded off to 1 decimal place).

Ques 6 Aircraft Propulsion

An aircraft with a turbojet engine is flying with 250 m/s speed at an altitude where the density of air is 1 kg/m³. The inlet area of the engine is 1 m². The average velocity of the exhaust gases at the exit of the nozzle, with respect to the aircraft, is 550 m/s. Assume the engine exit pressure is equal to the ambient pressure and the fuel-air ratio is negligible. The uninstalled thrust produced by the engine at these conditions is _______ N (rounded off to the nearest integer).

Ques 7 Aircraft Propulsion

A multistage axial compressor, with an overall isentropic efficiency of 0.83, is used to compress air at a stagnation temperature of 300 K through a pressure ratio of 10:1. Each stage of the compressor is similar, and the stagnation temperature rise across each compressor stage is 20 K. Assume C_p = 1005 J/kg K and γ = 1.4 for air. How many stages are there in the compressor?

Ques 8 Aircraft Propulsion

An aircraft with a turbojet engine is flying at 250 m/s. The uninstalled thrust produced by the engine is 60000 N. The heating value of the fuel is 44 x 10⁶ J/kg. The engine has a thermal efficiency of 35% while burning the fuel at a rate of 3 kg/s. Assume the engine exit pressure to be equal to the ambient pressure. What is the propulsion efficiency of the engine under these conditions (in percentage)?

Ques 9 Aircraft Propulsion

Which of the following statements is/are TRUE for an axial turbine?

Ques 10 Aircraft Propulsion

Which of the following statements is/are TRUE for a single-stage axial compressor?

Ques 11 Aircraft Propulsion

A chemical rocket with an ideally expanded flow through the nozzle produces 5 x 10⁶ N thrust at sea level. The specific impulse of the rocket is 200 s and acceleration due to gravity at sea level is 9.8 m/s². The propellant mass flow rate out of the rocket nozzle is _______ kg/s (rounded off to the nearest integer).

Ques 12 Aircraft Propulsion

A centrifugal compressor is designed to operate with air. At the leading edge of the tip of the inducer (eye of the impeller), the blade angle is 45° and the relative Mach number is 1.0. The stagnation temperature of the incoming air is 300 K. Consider γ = 1.4. Neglect pre-whirl and slip. The inducer tip speed is _______ m/s (rounded off to the nearest integer).

Ques 13 Flight Mechanics

In a conventional configuration airplane, the rudder can be used: