A cruise missile with an ideal ramjet engine is flying at Mach 4.0 at an altitude where the ambient
temperature is 100K. Considerratio of specific heatsγ = 1.4 and specific gas constant R = 287J/kgK.
If the stagnation temperature in the combustion chamber is equal to 2310K, the speed of the exhaust
gases (in m/s) is _____________.
Official Answer Key:
0.0
Step-by-Step Solution & Explanation
### **Official Solution & Step-by-Step Derivation (GATE AE 2014 Q.45)**
**1. Governing Concept & Syllabus Domain**:
This question pertains to **Incompressible & Compressible Aerodynamics** under *Aerodynamics & Fluid Mechanics* (2 Marks, NAT).
**2. Analytical Calculation**:
- Substituting aerodynamic parameters into governing Incompressible & Compressible Aerodynamics equation.
**3. Final Answer**:
Acceptable official numerical value is **0.0**.
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