A convectively cooled plug nozzle, using 4 percent of the engine air as the coolant, was tested in 1967 K (3540 R) temperature exhaust gas. No significant differences in cooling characteristics existed between flight and static results. At flight speeds above Mach 1.1, nozzle performance was improved by extending the outer shroud. Increasing engine power improved nozzle efficiency considerably more at Mach 1.2 than at 0.9. The effect of nozzle pressure ratio and secondary weight flow on nozzle performance are also presented. (Author)


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    Title :

    Flight Investigation of an Air-Cooled Plug Nozzle with Afterburning Turbojet


    Contributors:

    Publication date :

    1972


    Size :

    56 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English