An investigation was conducted in the Langley 16-Foot Transonic Tunnel to determine installation effects on convergent-divergent nozzles applicable to twin-engine reduced-power supersonic cruise aircraft. Tests were conducted at Mach numbers from 0.50 to 1.20, angles of attack from -5 deg to 9 deg, and at nozzle pressure ratios from jet off (1.0) to 8.0. The effects of empennage arrangement, nozzle length, and afterbody closure on total and component drag coefficients were investigated.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Investigation of Installation Effects on Twin-Engine Convergent-Divergent Nozzles


    Contributors:
    E. A. Bare (author) / B. L. Berrier (author)

    Publication date :

    1983


    Size :

    191 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English







    Aeroacoustic Resonance with Convergent-Divergent Nozzles

    Zaman, K. B. M. Q. / Dahl, M. D. / American Institute of Aeronautics and Astronautics | British Library Conference Proceedings | 1999