Wind tunnel tests were conducted at subsonic and transonic Mach numbers to determine the performance levels of exhaust nozzles installed in an aircraft. These tests were conducted with dual nozzles mounted in rigs simulating the entire airplane and with a single nozzle installed in a shaft-mounted rig simulating the aft end of half the airplane. Baseline isolated tests were also conducted with a single exhaust nozzle mounted on a cylindrical shaft. These tests showed that the better the simulated installation, the more valid the results. They also showed that a shaft mounted simulated airplane installation could provide valid trends for selecting the optimum nozzle installation.


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    Titel :

    Performance Installation Effects for Nozzles Installed on a Twin-Jet Fighter Airplane Model


    Weitere Titelangaben:

    Sae Technical Papers


    Beteiligte:
    Motycka, D. L. (Autor:in) / Skowronek, P. J. (Autor:in)

    Kongress:

    National Air Transportation Meeting ; 1968



    Erscheinungsdatum :

    29.04.1968




    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Print


    Sprache :

    Englisch




    Performance installation effects for nozzles installed on twin-jet fighter airplane model

    Motycka, D.L. / Skowronek, Jr., P.J. | Engineering Index Backfile | 1968


    Nonaxisymmetric Nozzles Installed in Advanced Fighter Aircraft

    P. E. Hiley / H. W. Wallacet / D. E. Booz | AIAA | 1976



    Performance characteristics of nonaxisymmetric nozzles installed on the F-18 airplane

    Capone, F.J. / Gowadia, N.S. / Wooten, W.H. | Tema Archiv | 1979


    Comparison of Non-Axisymmetric & Axisymmetric Nozzles Installed on a V/STOL Fighter Model

    Hoff, G.E. / Grossman, R.L. / Schnell, W.C. | SAE Technical Papers | 1977