The results of wind tunnel tests at NASA Langley targeted at the performance and configurational characteristics of 0.1 and 0.13 scale model spanwise blowing (SWB) jet wing concepts are reported. The concept involves redirection of engine compressor bleed air to provide SWB at the fuselage-wing juncture near the wing leading edge. The tests covered the orientation of the outer panel nozzles, the effects of SWB operation on the performance of leading and trailing edge flaps and the effects of SWB on lateral stability. The trials were run at low speeds and angles of attack from 24-45 deg (landing). Both lift and longitudinal stability improved with the SWB, stall and leading edge vortex breakdown were delayed and performance increased with the SWB rate. Lateral stability was degraded below 20 deg angle of attack while instabilities were delayed above 20 deg due to roll damping.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Experimental investigation of the aerodynamic effects of distributed spanwise blowing on a fighter configuration


    Contributors:

    Publication date :

    1948-08-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English


    Keywords :


    Aerodynamic effects of distributed spanwise blowing on a fighter configuration

    HUFFMAN, JARRETT K. / HAHNE, DAVID E. / JOHNSON, THOMAS D. | AIAA | 1987


    Aerodynamic effects of distributed spanwise blowing on a fighter configuration

    Huffman, Jarrett K. / Hahne, David E. / Johnson, Thomas D., Jr. | NTRS | 1987



    Pulsating spanwise blowing on a fighter aircraft

    MEYER, J. / SEGINER, A. | AIAA | 1992