(A) 251.9 and 458.2 (B) 234.9 and 486.8 (C) 251.9 and 486.8 (D) 234.9 and 458.2
A rocket engine is tested on a test bed under th e ideal condition of fully expanded jet. The exhaust
velocity is 2 km/s through a nozzle of area 2.5 m 2. The mass flow rate is 200 kg/s. The specific
impulse of the propellant and the thrust developed respectively are (assume g = 9.81 m/s2)
(A) 175.87 s and 200 kN (B) 203.87 s and 400 kN
Official Answer Key:
0.0
Step-by-Step Solution & Explanation
### **Official Solution & Step-by-Step Derivation (GATE AE 2011 Q.34)**
**1. Governing Concept & Syllabus Domain**:
This question pertains to **Air-Breathing & Rocket Propulsion** under *Propulsion* (1 Mark, NAT).
**2. Analytical Calculation**:
- Substituting aerodynamic parameters into governing Air-Breathing & Rocket Propulsion equation.
**3. Final Answer**:
Acceptable official numerical value is **0.0**.
Practice This in Real CBT Exam Interface
Test yourself with the official TCS-iON palette, virtual calculator, and immediate performance analytics.