An oblique shock wave with a wave angle β is generated from a wedge angle of θ . The ratio of the
Mach number downstream of the shock to its normal component is
(A) sin(β-θ) (B) cos( β-θ) (C) sin( θ-β) (D) cos(θ -β)
Official Answer Key:
0.0
Step-by-Step Solution & Explanation
### **Official Solution & Step-by-Step Derivation (GATE AE 2012 Q.37)**
**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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