An experimental investigation of the performance of a single-conical-shock diffuser was conducted at a Mach number of 5.4 and a Reynolds number based on model diameter of 375,000. Total-pressure recoveries of 13.7 and 13.1 percent were obtained at angles of attack of 0 degrees and 3 degrees, respectively. The corresponding kinetic energy efficiencies were 86.4 percent at an angle of attack of 0 degrees and 86.0 percent at an angle of attack of 3 degrees.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Investigation of Pressure Recovery of a Single-conical-shock Nose Inlet at Mach Number 5.4


    Contributors:

    Publication date :

    1953-04-06


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English