For inviscid, compressible flow past a thin airfoil, shown in the figure, free-stream Mach number
and pressure are denoted by ๐ด๐ดโ and ๐๐โrespectively. Ratio of pressure at point A and ๐๐โis 0.8
and specific heat ratio is 1.4. If the Mach number at point A is 1.0 and rest of the flow field is
subsonic, the value of ๐ด๐ดโis
(A) 2.95 (B) 0.79 (C) 1.18 (D) 0.64
AE 6/11
AE (GATE 2014)
- AE
Official Answer Key:
0.0
Step-by-Step Solution & Explanation
### **Official Solution & Step-by-Step Derivation (GATE AE 2014 Q.34)**
**1. Governing Concept & Syllabus Domain**:
This question pertains to **Incompressible & Compressible Aerodynamics** under *Aerodynamics & Fluid Mechanics* (1 Mark, 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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