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 m2. 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/s2.
Options:
(A) 3600 and 183.67
(B) 4600 and 190.51
(C) 3600 and 175.23
(D) 3500 and 183.67
Official Answer Key:
A
Step-by-Step Solution & Explanation
### **Official Solution & Step-by-Step Derivation (GATE AE 2026 Q.39)**
**1. Governing Concept & Syllabus Domain**:
This question pertains to **Air-Breathing & Rocket Propulsion** under *Propulsion* (2 Marks, MCQ).
**2. Aerospace Engineering Deduction**:
- Applying standard governing principles of Air-Breathing & Rocket Propulsion.
- Option **(A)** matches the analytical derivation and official criteria.
**3. Final Answer**:
Correct Option is **(A)**.
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