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Previous year question hub

Propulsion - Aerospace Engineering Previous Year Questions

Practice Propulsion - Aerospace Engineering previous year questions organised from real papers, with year-wise coverage and clear topic navigation.

2Papers
2Years
22Questions
1Topics

Propulsion question pattern

Every graph below is calculated only from this selection.

Questions by year

Year-wise coverage for Propulsion. Each bar uses a separate theme-derived color.

Difficulty distribution

How the classified questions are distributed by difficulty.

Medium 15 68.2%
Easy 6 27.3%
Hard 1 4.5%

Question type distribution

MCQ, numerical, multiple-select and other formats found in these papers.

Multiple Choices 13 59.1%
Numerical Answer Type (NAT) 9 40.9%

Subject weightage

Top subjects by unique question coverage.

Aerospace Engineering
22 Qs

Most asked topics

Top topics across the included previous year papers.

Propulsion
22 Qs

Subtopic coverage

Top subtopics inside this exact selection.

Turbomachinery
12 Qs
Gas turbine combustor
6 Qs
Rockets
4 Qs

Paper coverage

Question coverage for the most populated papers. Every active PYP paper remains listed below.

Aerospace Engineering (AE) 2026
13 Qs
Aerospace Engineering (AE) 2025
9 Qs

Browse by subtopics

Open a focused page built from the same verified paper data.

Turbomachinery

Explore previous-paper coverage, trends and focused practice for Turbomachinery.

12 questions2 papers2 years

Gas turbine combustor

Explore previous-paper coverage, trends and focused practice for Gas turbine combustor.

6 questions2 papers2 years

Rockets

Explore previous-paper coverage, trends and focused practice for Rockets.

4 questions2 papers2 years

Included previous year papers

Newest papers appear first. Sort by year, question coverage or name.

PaperYear / sessionQuestions in this viewOpen
Aerospace Engineering (AE) 2026202613View paper
Aerospace Engineering (AE) 202520259View paper

Sample previous year questions

A varied preview from the papers represented in this selection, with every available option.

1
2025 · Aerospace Engineering · Propulsion · Gas turbine combustor
Aerospace Engineering (AE) 2025
\(\delta Q\) and \(\delta W\) are the heat and work interactions of a system with its surroundings, and \(dU\) is the change in the internal energy of the system. For an adiabatic process in a closed, constant pressure combustor, which one of the following options is correct?
A
\(|\delta Q| = |dU| \neq 0\) and \(|\delta W| = 0\)
B
\(|\delta Q| = |\delta W| = 0\) and \(|dU| \neq 0\)
C
\(|\delta Q| = |\delta W| = |dU| = 0\)
D
\(|\delta W| = |dU| \neq 0\) and \(|\delta Q| = 0\)
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2
2026 · Aerospace Engineering · Propulsion · Turbomachinery
Aerospace Engineering (AE) 2026

Which one of the following makes an ideal air-standard Stirling cycle?

A

Two reversible isobars, and two reversible adiabatics

B

Two reversible isotherms, and two reversible isobars

C

Two reversible isotherms, and two reversible isochores

D
Isentropic compression, constant volume heat addition, isentropic expansion, and constant volume heat rejection
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3
2025 · Aerospace Engineering · Propulsion · Gas turbine combustor
Aerospace Engineering (AE) 2025
A gaseous fuel mixture comprising 3 moles of methane and 2 moles of ammonia is combusted in X moles of pure oxygen in stoichiometric amount. Assuming complete combustion, with only \(CO_2\), \(H_2O\) and \(N_2\) in the product gases, the value of X is ____.
\(3 CH_4 + 2 NH_3 + X O_2 \rightarrow \text{Products } (CO_2, H_2O, N_2)\)
A
7.5
B
5.5
C
8.5
D
9.5
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4
2026 · Aerospace Engineering · Propulsion · Gas turbine combustor
Aerospace Engineering (AE) 2026
The figure below depicts two ideal gas turbine cycles, cycle 1-2-3-4-1 and cycle 1-2-3'-4'-1, on a T-s diagram. Which one the following statements is FALSE?

Question source image

A

The thermal efficiency of the two cycles is the same

B

The specific work of the two cycles is the same

C

The processes 2-3 and 2-3' are isobaric

D
The amount of heat added in the combustion process is greater for the cycle 1-2-3'-4'-1
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5
2025 · Aerospace Engineering · Propulsion · Turbomachinery
Aerospace Engineering (AE) 2025
In a centrifugal compressor, the eye tip diameter is 10 cm. For a shaft rotational speed of 490 rotations per second, the tangential speed at the inducer tip is ____ m/s (rounded off to one decimal place).
Enter a numerical response
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6
2026 · Aerospace Engineering · Propulsion · Turbomachinery
Aerospace Engineering (AE) 2026
For a given air-standard power, the propulsive efficiency of a turbofan engine is more than that of a turbojet engine. Which of the following is/are the reason(s) for this?
A

The mass flow rate is more for a turbofan engine

B

The exit velocity is lower for a turbofan engine

C

A turbofan engine operates at a lower altitude

D

The fan of a turbofan engine consumes lesser power

Open complete paper