The GATE Grind

GATE 2025 AE – Question 18

Aerodynamics · Airfoils and wings: coefficients, Kutta-Joukowski theorem, thin airfoil theory, finite wing theory, critical and drag divergence Mach numbers · 1 mark · Multiple choice

For a NACA 4415 airfoil, the location of maximum camber, as a fraction of the chord length from the leading edge, is ______.

  1. 0.44
  2. 0.40
  3. 0.15
  4. 0.04

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Show answer and explanation

Correct answer: (B) 0.40

Explanation

In the NACA four-digit code the first digit is the maximum camber in percent of the chord (4%), the second digit is its position in tenths of the chord (0.4), and the last two digits are the thickness (15%).