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

    Erscheinungsdatum :

    1976


    Format / Umfang :

    51 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch