Thin airfoil theory predicts the zero-lift angle of attack 𝛼L=0 of NACA 2412 airfoil
as -2.1°. The corresponding prediction of 𝛼L=0 for NACA 5410 airfoil is
________ degrees (rounded off to 1 decimal place).
Official Answer Key:
0.0
Step-by-Step Solution & Explanation
### **Official Solution & Step-by-Step Derivation (GATE AE 2026 Q.63)**
**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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