Consider a supersonic stream at a Mach number M=2, undergoing a gradual expansion. The stream
is turned by an angle of 3 degrees due to the expansion. The following data is given.
M (Prandtl-Meyer function)
1.8 20.73
1.9 23.59
2.0 26.38
2.1 29.10
2.2 31.73
2.3 34.28
2.4 36.75
The Mach number downstream of the expansion is
(A) 1.88 (B) 2.00 (C ) 2.11 (D) 2.33
1 2
3
4
5
6
2013 AEROSPACE ENGINEERING - AE
AE 13/19
Official Answer Key:
0.0
Step-by-Step Solution & Explanation
### **Official Solution & Step-by-Step Derivation (GATE AE 2013 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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