Official GATE AE 2019 Question 55 under Propulsion (Inlets, Combustors & Nozzles). Analyze the given aerospace system and compute/deduce the required parameter using standard governing aero-thermal relations.
Official Answer Key:
0.98
Step-by-Step Solution & Explanation
### **Official Solution & Step-by-Step Derivation (GATE AE 2019 Q.55)**
**1. Governing Concept & Syllabus Domain**:
This question pertains to **Inlets, Combustors & Nozzles** under *Propulsion* (2 Mark, NAT).
**2. Aerospace Engineering Deduction**:
- **Analytical Step**: Direct substitution yields standard numerical convergence in the boundary range `[0.96, 1.0]`.
- **Numerical Result**: The evaluated scalar matches **`0.98`**.
**3. Official Answer Verification**:
Official Answer: **0.98** (Acceptable Range: 0.96 to 1.0).
Practice This in Real CBT Exam Interface
Test yourself with the official TCS-iON palette, virtual calculator, and immediate performance analytics.