Wind-tunnel tests were conducted in the Langley low-turbulence pressure tunnel to evaluate the effects on performance of modifying a 17-percent-thick low-speed airfoil. The airfoil contour was altered to reduce the pitching-moment coefficient by increasing the forward loading and to increase the climb lift-drag ratio by decreasing the aft upper surface pressure gradient. The tests were conducted over a Mach number range from 0.07 to 0.32, a chord Reynolds number range 1.0 x 10 to the 6th power to 12.0 x 10 to the 6th power, and an angle-of-attack range from about -10 deg to 20 deg.


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    Title :

    Wind-tunnel results for a modified 17-percent-thick low-speed airfoil section


    Contributors:

    Publication date :

    1981-11-01


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English


    Keywords :