Consider a 20 0 half-angle wedge in a supersonic flow at Mach 3 .0 at standard sea -level
conditions. If the shock-wave angle on the wedge is 360, the Mach number of the tangential
component of the flow post-shock is _______ (accurate to two decimal places).
Official Answer Key:
0.0
Step-by-Step Solution & Explanation
### **Official Solution & Step-by-Step Derivation (GATE AE 2018 Q.46)**
**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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