A turbojet powered aircraft is flying at Mach nu
mber 0.8 at an altitude of 10 km. The inlet and exit
areas of the engine are 0.7 m 2 and 0.4 m 2 respectively. The exhaust gases have velocity of 500 m/s
and pressure of 60 kPa. The free stream pressure , density and speed of sound are 26.5 kPa, 0.413
kg/m3 and 299.5 m/s respectively. The thrust of the engine (in kN) is
Official Answer Key:
0.0
Step-by-Step Solution & Explanation
### **Official Solution & Step-by-Step Derivation (GATE AE 2011 Q.28)**
**1. Governing Concept & Syllabus Domain**:
This question pertains to **Incompressible & Compressible Aerodynamics** under *Aerodynamics & Fluid Mechanics* (1 Mark, 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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