Experimental data were obtained with a 21.59 cm (8.5 in.) diameter cold-flow model in a static altitude facility to determine the thrust and pumping characteristics of several variations of a ram-air-cooled plug nozzle. Tests were conducted over a range of nozzle pressure ratios simulating supersonic cruise and takeoff conditions. Primary throat area was also varied to simulate afterburner on and off. Effect of plug size, outer shroud length, primary nozzle geometry, and varying amounts of secondary flow were investigated. At a supersonic cruise pressure ratio of 27, nozzle efficiencies were 99.7 percent for the best configurations. (Author)


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    Title :

    Cold-Flow Performance of Several Variations of a Ram-Air-Cooled Plug Nozzle for Supersonic-Cruise Aircraft


    Contributors:

    Publication date :

    1974


    Size :

    37 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English