For a NACA 4415 airfoil, the location of maximum camber, as a fraction of the chord length from the leading edge, is \_\_\_\_\_\_.
Show Hint
- 0.44
- 0.40
- 0.15
- 0.04
The Correct Option is B
Solution and Explanation
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.
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