The stagnation temperatures at the inlet and exit of a combustion chamber are 600 K and 1200 K,
respectively. If the heating value of the fuel is 44 MJ/kg and specific heat at constant pressure for
air and hot gases are 1.005 kJ/kg.K and 1.147 kJ/kg.K respectively, the fuel-to-air ratio is
(A) 0.0018 (B) 0.018 (C) 0.18 (D) 1.18
Official Answer Key:
0.0
Step-by-Step Solution & Explanation
### **Official Solution & Step-by-Step Derivation (GATE AE 2012 Q.40)**
**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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