The NASA-Ames 6 x 6-foot Transonic/Supersonic Wind Tunnel has been used to conduct a study of canard-wing flowfield interactions at sub-, trans-, and supersonic speeds, giving attention to vortex interactions, vortex breakdown, shock-wave development, and vortex-shock interactions. The results obtained show that the canard-wing flowfield interaction delays vortex breakdown to a higher angle-of-attack at sub- and transonic speeds; while the flowfield interference eliminates shock-induced secondary boundary layer separation on the wing, it does not alter the location and development of a rear shock wave extending laterally across the wing. A canard-induced upwash field accelerates the upward migration of the wing vortex at sub-through-supersonic speeds, but is most pronounced at transonic speeds due to the interaction of the vortical flow with the rear shock wave.


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    Titel :

    Canard-wing vortex interactions at subsonic through supersonic speeds


    Beteiligte:

    Kongress:

    AIAA Atmospheric Flight Mechanics Conference ; 1990 ; Portland, OR, United States


    Erscheinungsdatum :

    01.01.1990


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Canard-wing vortex interactions at subsonic through supersonic speeds

    ERICKSON, GARY / SCHREINER, JOHN / ROGERS, LAWRENCE | AIAA | 1990


    Effect of canard vertical location, size, and deflection on canard-wing interference at subsonic speeds

    Gloss, Blair B. / Ray, Edward J. / Washburn, Karen E. | TIBKAT | 1978




    Wing-Design Program for Subsonic or Supersonic Speeds

    Carlson, H. W. / Walkley, K. B. | NTRS | 1986