Question

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

• A. 0.44
• B. 0.40
• C. 0.15
• D. 0.04

Hint:

For NACA airfoils, the first digit represents the camber as a percentage, the second digit represents the location of maximum camber as a fraction of the chord length, and the last two digits represent the maximum thickness as a percentage of the chord length.

Answer 1

The Correct Option is B

For NACA airfoils, the number 4415 represents the following components: The first digit (4) represents the maximum camber as a percentage of the chord length (in this case, 4%).
The second digit (4) represents the location of maximum camber as a fraction of the chord length from the leading edge (in this case, 0.40 or 40%).
The last two digits (15) represent the maximum thickness as a percentage of the chord length (15%). Thus, the location of the maximum camber is 0.40 of the chord length from the leading edge.