Surface Mach number distributions, total pressure loss coefficients, and schlieren images of the flow are presented over a range of inlet Mach numbers and air angles. Several different trailing edge geometries were tested. At design conditions a leading edge separation bubble was observed resulting in higher losses than anticipated. The minimum losses were obtained at a negative incidence condition in which the flow was accelerating over most of the supercritical region. Relatively minor differences in losses were measured with the different trailing edge geometries studied.


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    Titel :

    Experimental evaluation of shockless supercritical airfoils in cascade


    Beteiligte:
    Boldman, D. R. (Autor:in) / Buggele, A. E. (Autor:in) / Shaw, L. M. (Autor:in)

    Kongress:

    American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting ; 1983 ; Reno, NV


    Erscheinungsdatum :

    01.01.1983


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Experimental evaluation of shockless supercritical airfoils in cascade

    BOLDMAN, D. / BUGGELE, A. / SHAW, L. | AIAA | 1983


    Experimental evaluation of shockless supercritical airfoils in cascade

    Boldman, D. R. / Buggele, A. E. / Shaw, L. M. | NTRS | 1983


    Shockless transonic airfoils

    TRUITT, R. | AIAA | 1970


    Numerical design of shockless airfoils

    Garabedian, P. R. | NTRS | 1979