GATE AE · 2026 · AE
Question 39: Rockets
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Question 39
AEMCQ2 marksNeeds review
An ideal rocket has characteristic exhaust velocity of 1200 m/s, mass flow rate of 75 kg/s, thrust coefficient of 1.5, and nozzle throat area of 0.025 m
. The chamber pressure in kPa and the specific impulse due to gravity in seconds are ______, respectively. Assume that the acceleration due to gravity is 9.8 m/s
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2026AE
GATE AE 2026 · Paper 1
Aerospace Engineering · Original paper archive
- Section
- Aerospace Engineering
- Question type
- Multiple choice (MCQ)
- Marks
- 2 marks
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