The major aspects of a code for the design of shockless airfoils in two-dimensional transonic flow are reviewed. The code is based on a method of analytic continuation into the domain of two complex characteristic variables, which makes it possible to associate a shockless airfoil with a given pressure distribution. This procedure is compared with another more direct method based on a two-dimensional analysis code that has had wide acceptance by the aircraft industry.


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    Titel :

    Shockless airfoils for wings, compressors, and turbines


    Beteiligte:

    Kongress:

    Nonlinear partial differential equations in engineering and applied science ; 1979 ; Kingston, RI


    Erscheinungsdatum :

    01.01.1980


    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Shockless transonic airfoils

    TRUITT, R. | AIAA | 1970


    Numerical design of shockless airfoils

    Garabedian, P. R. | NTRS | 1979


    Experimental evaluation of shockless supercritical airfoils in cascade

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


    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