GATE AE 2025 • Q18
MCQ • 1 Mark
Aerodynamics & Fluid Mechanics
Incompressible & Compressible Aerodynamics
Subtopic: Airfoil & Wing Theory
Question Statement:
For a NACA 4415 airfoil, the location of maximum camber, as a fraction of the
chord length from the leading edge, is ______.
Options:
-
(A) 0.44
-
(B) 0.40
-
(C) 0.15
-
(D) 0.04
Step-by-Step Solution & Explanation
### **Official Solution & Step-by-Step Derivation (GATE AE 2025 Q.18)**
**1. Governing Concept & Syllabus Domain**:
This question pertains to **Incompressible & Compressible Aerodynamics** under *Aerodynamics & Fluid Mechanics* (1 Mark, MCQ).
**2. Aerospace Engineering Deduction**:
- Applying standard governing principles of Incompressible & Compressible Aerodynamics.
- Option **(A)** matches the analytical derivation and official criteria.
**3. Final Answer**:
Correct Option is **(A)**.
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