The internal performance of an axisymmetric convergent-divergent nozzle and a nonaxisymmetric convergent-divergent nozzle, both of which utilized a gimbal type mechanism for thrust vectoring was evaluated in the Static Test Facility of the Langley 16-Foot Transonic Tunnel. The nonaxisymmetric nozzle used the gimbal concept for yaw thrust vectoring only; pitch thrust vectoring was accomplished by simultaneous deflection of the upper and lower divergent flaps. The model geometric parameters investigated were pitch vector angle for the axisymmetric nozzle and pitch vector angle, yaw vector angle, nozzle throat aspect ratio, and nozzle expansion ratio for the nonaxisymmetric nozzle. All tests were conducted with no external flow, and nozzle pressure ratio was varied from 2.0 to approximately 12.0.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Internal Performance of Two Nozzles Utilizing Gimbal Concepts for Thrust Vectoring


    Contributors:

    Publication date :

    1990


    Size :

    128 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English





    Tilting rotorcraft utilizing ducted fan thrust vectoring nozzles

    ZHANG HONGSHAN / XIE ZHENGRUI | European Patent Office | 2023

    Free access

    Aerodynamics Performance Prediction of Thrust-Vectoring Nozzles

    A. Matesanz / A. Velazquez / M. Rodriguez | AIAA | 1998



    Aircraft thrust vectoring using flexible nonaxisymmetric nozzles

    Whitaker, Kevin W. / Gowadia, Noshir S. | AIAA | 1994