A rocket motor has a chamber pressure of 100 bar and chamber temperature of 3000 K. The
ambient pressure is 1 bar. Assume that the specifi c heat at constant pressure is 1 kJ/kg-K. Also
assume that the flow in the nozzle is isentropic and optimally expanded. The exit static temperature
in K is
(A) 805 (B) 845 (C) 905 (D) 945
2013 AEROSPACE ENGINEERING - AE
AE 10/19
Q. 26 to Q. 55 carry two marks each.
Official Answer Key:
0.0
Step-by-Step Solution & Explanation
### **Official Solution & Step-by-Step Derivation (GATE AE 2013 Q.25)**
**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**.
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