Wolfram|Alpha

Computing...

Input information:

standard airfoil |  \nNACA number | 0012\nangle of attack | 5°  (degrees)


Results for incompressible potential flow:

lift coefficient | 0.597\nleading edge pitching moment coefficient | -0.155\nestimated critical Mach number | 0.492


Airfoil properties in fraction of chord length:

center of pressure | 0.170\nmaximum camber | 0.\nmaximum camber location from leading edge | 0.\nmaximum thickness | 0.12


Pressure coefficient for incompressible potential flow:

Frame

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