Nearly all supersonic V/STOL aircraft concepts are dependent on the thrust deflecting capability of a nozzle. In one unique concept, referred to as the reverse flow dual fan, not only is there a thrust deflecting nozzle for the fan and core engine exit flow, but because of the way the propulsion system operates during vertical takeoff and landing, the supersonic inlet is also used as a thrust deflecting nozzle. This paper presents results of an experimental study to evaluate the performance of a supersonic inlet used as a thrust deflecting nozzle for this reverse flow dual fan concept. Results are presented in terms of nozzle thrust coefficient and thrust vector angle for a number of inlet/nozzle configurations. Flow visualization and nozzle exit flow survey results are also shown.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Experimental Results for a Two-Dimensional Supersonic Inlet Used as a Thrust Deflecting Nozzle


    Contributors:

    Publication date :

    1984


    Size :

    14 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English






    Development of the 'D' vented thrust deflecting nozzle

    ROSENBERG, E. / ESKER, D. | AIAA | 1980


    Ground test of a large scale 'D' vented thrust deflecting nozzle

    Rosenberg, E. W. / Christiansen, R. S. | NTRS | 1981


    Ground test of a large scale 'D' vented thrust deflecting nozzle

    ROSENBERG, E. / CHRISTIANSEN, R. | AIAA | 1981