Question Statement:
For a symmetric airfoil, the lift coefficient for zero degree angle of attack is
(A) - 1.0 (B) 0.0 (C) 0.5 (D) 1.0
Step-by-Step Solution & Explanation
### **Official Solution & Step-by-Step Derivation (GATE AE 2012 Q.5)**
**1. Governing Concept & Syllabus Domain**:
This question pertains to **Verbal & Numerical Aptitude** under *General Aptitude* (1 Mark, 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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