A single-stage axial compressor, with a 50 % degree of reaction, runs at a mean
blade speed of 250 m/s. The overall pressure ratio developed is 1.3. Inlet pressure
and temperature are 1 bar and 300 K, respectively. Axial velocity is 200 m/s.
Specific heat at constant pressure, Cp = 1005 J/kg/K and specific heat ratio,
γ = 1.4. The rotor blade angle at the outlet is ___ degrees (rounded off to two
decimal places).
Official Answer Key:
0.0
Step-by-Step Solution & Explanation
### **Official Solution & Step-by-Step Derivation (GATE AE 2025 Q.65)**
**1. Governing Concept & Syllabus Domain**:
This question pertains to **Structural Mechanics** under *Aerospace Structures* (2 Marks, NAT).
**2. Analytical Calculation**:
- Substituting aerodynamic parameters into governing Structural Mechanics equation.
**3. Final Answer**:
Acceptable official numerical value is **0.0**.
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