Aerospace Engineering > GATE 2019 > Airfoil Nomenclature
For a NACA 2415 airfoil of chord length c, which of the following is true?
A
Maximum camber is located at 0.2c from the leading edge.
B
Maximum thickness is located at 0.15c from the leading edge.
C
Maximum camber is 0.02c.
D
Maximum thickness is 0.05c.

Correct : c

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Related Topics

NACA 2415 airfoil Aerospace Engineering GATE 2019 NACA airfoil properties maximum camber maximum thickness airfoil characteristics GATE Aerospace Engineering chord length

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