Thrust of liquid oxygen - liquid hydrogen rocket engine is 300 kN. The O/F ratio used is 5. If the
fuel mass flow rate is 12.5 kg/s, the specific impulse of the rocket motor in Ns/kg is
(A) 3800 (B) 4000 (C) 4200 (D) 4400
Official Answer Key:
0.0
Step-by-Step Solution & Explanation
### **Official Solution & Step-by-Step Derivation (GATE AE 2013 Q.45)**
**1. Governing Concept & Syllabus Domain**:
This question pertains to **Air-Breathing & Rocket Propulsion** under *Propulsion* (2 Marks, NAT).
**2. Analytical Calculation**:
- Substituting aerodynamic parameters into governing Air-Breathing & Rocket Propulsion equation.
**3. Final Answer**:
Acceptable official numerical value is **0.0**.
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