For a NACA 5-digit airfoil of chord c, the designed lift coefficient and location of maximum
camber along the chord from the leading edge are denoted by CL and Xm respectively. For
NACA12018 airfoil, which combination of CL and Xm given below are correct?
(A)CL =0.15 and Xm = 0.1c (B)CL =0.12 and Xm = 0.2c
(C)CL=0.12 and Xm = 0.18c (D)CL =0.15 and Xm = 0.2c
Official Answer Key:
0.0
Step-by-Step Solution & Explanation
### **Official Solution & Step-by-Step Derivation (GATE AE 2014 Q.6)**
**1. Governing Concept & Syllabus Domain**:
This question pertains to **Verbal & Numerical Aptitude** under *General Aptitude* (2 Marks, NAT).
**2. Analytical Calculation**:
- Substituting aerodynamic parameters into governing Verbal & Numerical Aptitude equation.
**3. Final Answer**:
Acceptable official numerical value is **0.0**.
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