The rate of change of moment coefficient with respect to the angle of attack,
d
dC m , at half chord
point of a thin airfoil, as per approximations from the thin airfoil theory is
(A) π/4 radian-1 (B) π/2 radian-1 (C) π radian-1 (D) 2π radian-1
Official Answer Key:
0.0
Step-by-Step Solution & Explanation
### **Official Solution & Step-by-Step Derivation (GATE AE 2016 Q.31)**
**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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