Aerospace Engineering GATE 2022 Questions with Answer

Ques 1 Aerodynamics

NACA 2412 airfoil has _______.

Ques 2 Aerodynamics

For International Standard Atmosphere (ISA) up to 11 km, which of the following statement(s) is/are true?

Ques 3 Aerodynamics

Consider a conventional subsonic fixed-wing airplane. e is the Oswald efficiency factor and AR is the aspect ratio. Corresponding to the minimum of (C_D/C_L^3/2), which of the following relations is true?

Ques 4 Aerodynamics

Consider a circulation distribution over a finite wing given by the equation below.

Ques 5 Aerodynamics

Consider a thin symmetric airfoil at a 2-degree angle of attack in a uniform flow at 50 m/s. The pitching moment coefficient about its leading edge is _______. (rounded off to three decimal places)

Ques 6 Aircraft Propulsion

The region of highest static temperature in a rocket engine and the region of highest heat flux are _______, respectively.

Ques 7 Aircraft Propulsion

A high-pressure-ratio multistage axial compressor encounters an extreme loading mismatch during starting. Which of the following technique(s) can be used to alleviate this problem?

Ques 8 Aircraft Propulsion

In a static test, a turbofan engine with a bypass ratio of 9 has a core hot exhaust speed 1.5 times that of fan exhaust speed. The engine is operated at a fuel to air ratio of f = 0.03. Both the fan and the core streams have no pressure thrust. The ratio of fan thrust to thrust from the core engine is _______. (round off to one decimal place)

Ques 9 Aircraft Propulsion

In a single stage turbine, the hot gases come out of stator/nozzle at a speed of 500 m/s and at an angle of 70 degrees with the turbine axis as shown. The design speed of the rotor blade is 250 m/s at the mean blade radius. The rotor blade angle, β, at the leading edge is _______ degrees. (round off to one decimal place)

Ques 10 Aircraft Propulsion

A rocket operates at an absolute chamber pressure of 20 bar to produce thrust, F₁. The hot exhaust is optimally expanded to 1 bar (absolute pressure) using a convergent-divergent nozzle with exit to throat area ratio (A_e/A_t) of 3.5 and thrust coefficient, C_F,1 = 1.42.
The same rocket when operated at an absolute chamber pressure of 50 bar produces thrust F₂ and the thrust coefficient is C_F,2.
Which of the following statement(s) is/are correct?

Ques 11 Aircraft Propulsion

An ideal ramjet is to operate with exhaust gases optimally expanded to ambient pressure at an altitude where the temperature is 220 K. The exhaust speed at the nozzle exit is 1200 m/s at a temperature of 1100 K. Given: γ = 1.4 at 220 K; R = 287 J/(kg-K) for air; γ = 1.33 at 1100 K; R = 287 J/(kg-K) for exhaust gases. The cruise speed of this ramjet is _______ m/s. (rounded off to the nearest integer)

Ques 12 Aircraft Propulsion

A multistage axial compressor takes in air at 1 atm, 300 K and compresses it to a minimum of 5 atm. The mean blade speed is 245 m/s and the work coefficient, ΔC_θ/U, is 0.55 for each stage. For air, use C_p = 1005 J/(kg-K), R = 287 J/(kg-K) and γ = 1.4. If the compression is isentropic, the number of stages required is _______. (rounded off to the next higher integer)

Ques 13 Aircraft Structures

The closed thin-walled rectangular channel shown in figure (i) is opened by introducing a sharp cut at the center of the bottom edge, as shown in figure (ii). Which one of the following statements is correct?