The effect of forebody tangential slot blowing on the flowfield about an F/A-18 aircraft is investigated numerically using solutions of the Navier-Stokes equations. Computed solutions are obtained for an aircraft geometry which includes the fuselage, a wing with deflected leading-edge flap, empennage, and a faired-over engine inlet. The computational slot geometry corresponds to that used in full-scale wind-tunnel tests. Solutions are computed using flight test conditions and jet mass flow ratios equivalent to wind-tunnel test conditions. The effect of slot location is analyzed by computing two nontime-accurate solutions with a 16-in. slot located 3 in. and 11 in. aft of the nose of the aircraft. These computations resolve the trends observed in the full-scale wind-tunnel test data. The flow aft of the leading-edge extension vortex burst is unsteady. A time-accurate solution is obtained to investigate the flow characteristics aft of the vortex burst, including the effect of blowing on tail buffet.


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    Titel :

    Forebody Tangential Slot Blowing on an Aircraft Geometry


    Beteiligte:
    Gee, Ken (Autor:in) / Rizk, Yehia M. (Autor:in) / Schiff, Lewis B. (Autor:in)

    Kongress:

    Fluid Dynamics, Plasmadynamics, and Lasers Conference ; 1993 ; Orlando, Fl, United States


    Erschienen in:

    Erscheinungsdatum :

    1994-08-01


    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Forebody tangential slot blowing on an aircraft geometry

    Gee, Ken / Rizk, Yehia M. / Schiff, Lewis B. | AIAA | 1994




    Effect of forebody tangential slot blowing on flow about a full aircraft geometry

    Gee, Ken / Rizk, Yehia M. / Schiff, Lewis B. | NTRS | 1993


    Numerical Analysis of Tangential Slot Blowing on a Generic Chined Forebody

    Agosta-Greenman, R. / Schiff, L. / Gee, K. et al. | British Library Conference Proceedings | 1994