An investigation was conducted in the Langley 16-Foot Transonic Tunnel to determine installation effects on single-engine convergent-divergent nozzles applicable to reduced-power supersonic cruise aircraft. Tests were conducted at Mach numbers from 0.50 to 1.20, at angles of attack from -3 degrees to 9 degrees, and at nozzle pressure ratios from 1.0 (jet off) to 8.0. The effects of empennage arrangement, nozzle length, a cusp fairing, and afterbody closure on total aft-end drag coefficient and component drag coefficients were investigated. Basic lift- and drag-coefficient data and external static-pressure distributions on the nozzle and afterbody are presented and discussed.


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    Title :

    Investigation of installation effects of single-engine convergent-divergent nozzles


    Contributors:

    Publication date :

    1982-11-01


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English


    Keywords :





    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