An investigation was conducted in the 8- by 6-foot supersonic wind tunnel on a cylindrical-shroud ejector (diameter ratio of 1.2 and spacing ratio of 0.80). Data were obtained at weight-flow ratios of 0.014, 0.095, 0.234, and 0.380 for primary pressure ratios ranging from 1 to 16 and at free-stream Mach numbers of 0.1, 0.6, 1.6, and 2.0. The results of this investigation indicate no effort of free-stream Mach number on the pumping characteristics of an ejector of this type. Boattail pressure-drag and base pressure-drag coefficients were found to decrease with increasing primary pressure ratio similar to conventional nozzles. It was also found that these drag coefficients decreased as weight-flow ratio was increased. The results also indicate that the primary-nozzle mass-flow coefficient was affected by the secondary flow. Apparently the internal geometry of the secondary passage, at the exit station of the primary nozzle, was critical in effecting a decrease in primary-nozzle mass-flow coefficient as weight-flow ratio was increased to values greater than 0.10. (Author)


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    Title :

    Pumping and Drag Characteristics of an Aircraft Ejector at Subsonic and Supersonic Speeds


    Contributors:

    Publication date :

    1954


    Size :

    24 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English