(C) mass flow rate through exhaust nozzle (D) compressor pressure ratio
The pressure ratio in any one stage of a jet engine compressor is limited by
(A) entry stagnation temperature in that stage
(B) entry Mach number in that stage
(C) pressure gradient induced separation in that stage
Official Answer Key:
0.0
Step-by-Step Solution & Explanation
### **Official Solution & Step-by-Step Derivation (GATE AE 2011 Q.22)**
**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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