The inlet was investigated with both a two-oblique-shock and an isentropic compression ramp. Provisions for a variety of bypass systems were incorporated and none decreased pressure recovery by more than about 1 percent. By utilizing throat boundary-layer control, critical pressure recoveries of 64 and 70 percent were obtained with the two-shock and isentropic ramps, respectively. Diffuser-exit air distortion was about 5 percent at critical operation Theoretical cowl pressure drag was equal to about 10 percent of the net thrust of an assumed engine.


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    Title :

    Performance of variable two-dimensional inlet designed for engine-inlet matching I : performance at design Mach number of 3.07


    Contributors:
    Beheim, M A (author) / Gertsma, L W (author)

    Publication date :

    1956-10-20


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English