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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    Titel :

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


    Beteiligte:
    Mcghee, R. J. (Autor:in) / Beasley, W. D. (Autor:in)

    Erscheinungsdatum :

    01.06.1976


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :