Discussion
For a NACA 4415 airfoil, the location of maximum camber, as a fraction of the chord length from the leading edge, is ______.
Answer: B
The maximum camber is at 0.40 of the chord.
In the NACA four-digit series the digits are read as M P XX: the first digit is the maximum camber in per cent of chord, the second is its position in tenths of chord from the leading edge, and the last two are the maximum thickness in per cent of chord. For NACA 4415: maximum camber 4% (0.04c) located at 0.4c, with 15% thickness.
0.04 is the camber itself, not its location, and 0.15 is the thickness ratio. 0.44 simply runs the first two digits together and has no meaning in the designation.
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