Wind tunnel tests were conducted to determine the effects of airfoil thickness-ratio on the low speed aerodynamic characteristics of an initial family of airfoils. The results were compared with theoretical predictions obtained from a subsonic viscous method. The tests were conducted over a Mach number range from 0.10 to 0.28. Chord Reynolds numbers varied from about 2.0 x 1 million to 9.0 x 1 million.


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    Title :

    Effects of thickness on the aerodynamic characteristics of an initial low-speed family of airfoils for general aviation applications


    Contributors:

    Publication date :

    1976-06-01


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English


    Keywords :