The paper describes the development of a thick (t/c = 0.18) transonic, multifoil, blown augmentor-wing section and discusses the results of a series of wind-tunnel tests on the configuration. The results show that the blown multifoil section enjoys two advantages over a conventional unblown single-foil supercritical section or the same overall thickness-chord ratio: 1) "effective" drag reduced by blowing, and 2) increased drag rise Mach number (M(sub D) = 0.75); they also demonstrate that augmentor blowing improves the buffet boundaries of the section. Thus, overall, it has been shown that the augmentor flap configuration is capable of extending the speed range of a jet transport aircraft to the very low approach speeds required by STOL aircraft [as demonstrated by the NASA/DITC (Canadian Department of Industry Trade and Commerce) augmentor-wing STOL research aircraft] and also to the high subsonic speed required for cruise, where it is shown to be competitive with the plain supercritical airfoil.


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    Titel :

    The Transonic Multifoil Augmentor Wing


    Beteiligte:

    Kongress:

    V/STOL Conference ; 1977 ; Palo Alto, CA, United States


    Erschienen in:

    Erscheinungsdatum :

    01.11.1979


    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    The Transonic Multifoil Augmentor Wing

    J.E. Farbridge / Ronald C. Smith | AIAA | 1978


    The transonic multi-foil Augmentor-Wing

    Farbridge, J. E. / Smith, R. C. | NTRS | 1977


    The transonic multi-foil Augmentor-Wing

    FARBRIDGE, J. / SMITH, R. | AIAA | 1977


    Transonic separated solutions for an augmentor wing

    Flores, Jolen / Van Dalsem, William R. | NTRS | 1986


    Transonic separated solutions for an augmentor wing

    FLORES, JOLEN / VAN DALSEM / WILLIAM R. | AIAA | 1986