(A) -0.05 0.02i (B) -0.5 0.2i (C) -0.028 1.26i (D) 0.028 1.26i
Consider the inviscid, adiabatic flow of air at free stream conditions, M
1 = 2, p 1 = 1 atm and T 1 =
288 K around a sharp expansion corner ( θ = 20°) as shown below. The Prandtl-Meyer function, ν,
is given as a function of Mach number, M, as 1 M tan ) 1 M (1
1tan1
1) M ( 2 121
Assume air to be calorically perfect with = 1.4. The Mach number, M 2, downstream of the
expansion corner is approximately
Official Answer Key:
0.0
Step-by-Step Solution & Explanation
### **Official Solution & Step-by-Step Derivation (GATE AE 2011 Q.43)**
**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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