An ideal ramjet with an optimally expanded exhaust is travelling at Mach 3. The
ambient temperature and pressure are 260 K and 60 kPa, respectively. The inlet air
mass flow rate is 50 kg/s. Exit temperature of the exhaust gases is 700 K. Fuel
mass flow rate is negligible compared to air mass flow rate. Gas constant is
R= 287 J/kg/K, and specific heat ratio is γ = 1.4. The thrust generated by the
engine is ___ kN (rounded off to one decimal place).
Official Answer Key:
0.0
Step-by-Step Solution & Explanation
### **Official Solution & Step-by-Step Derivation (GATE AE 2025 Q.64)**
**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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