Results are presented on models having range of airfoil thickness from 3 to 12% chord for single and double wedge airfoils and tapered planforms and from 9 to 20% chord for double wedge airfoils and square planforms; for test parameters, in general, thickness effects are destabilizing at higher Mach but stabilizing at subsonic and transonic Mach numbers.


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    Titel :

    Aerodynamic effects of some configuration variables on aero-elastic characteristics of lifting surfaces at Mach numbers from 0.7 to 6.86


    Weitere Titelangaben:

    NASA -- Tech Note


    Beteiligte:
    Hanson, P.W. (Autor:in)


    Erscheinungsdatum :

    1961


    Format / Umfang :

    51 pages


    Medientyp :

    Report


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :