For an airfoil section the pitching moment coefficient is determined about a
reference point that is 0.3 times the chord behind the leading edge. It varies with
the lift coefficient as shown in the table below. The distance of the aerodynamic
center from the leading edge of the airfoil as a fraction of the chord is ________
(rounded off to one decimal place).
cl 0.2 0.4 0.6 0.8
cm - 0.02 0 0.02 0.04
Official Answer Key:
0.0
Step-by-Step Solution & Explanation
### **Official Solution & Step-by-Step Derivation (GATE AE 2026 Q.54)**
**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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