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.


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    Titel :

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


    Beteiligte:
    E. A. Bare (Autor:in) / B. L. Berrier (Autor:in)

    Erscheinungsdatum :

    1983


    Format / Umfang :

    191 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch







    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