The GATE Grind

GATE 2019 AE – Question 17

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 2415 airfoil of chord c, which statement is correct?

  1. Maximum camber is located at 0.2c.
  2. Maximum thickness is located at 0.15c.
  3. Maximum camber is 0.02c.
  4. Maximum thickness is 0.05c.

Practise this question in The GATE Grind →

Show answer and explanation

Correct answer: (C) Maximum camber is 0.02c.

Explanation

In the four-digit NACA designation, 2 gives maximum camber as 2% of chord; 4 places it at 40% of chord; 15 gives maximum thickness as 15% of chord. Thus maximum camber is 0.02c, C. Thickness magnitude does not specify its chordwise location.

More Airfoils and wings: coefficients, Kutta-Joukowski theorem, thin airfoil theory, finite wing theory, critical and drag divergence Mach numbers questions

All Airfoils and wings: coefficients, Kutta-Joukowski theorem, thin airfoil theory, finite wing theory, critical and drag divergence Mach numbers questions →