Pressure distribution data are provided for a supersonic rectangular inlet at subsonic speeds. Variations in cowl and ramp geometry as well as sideplate sweep were investigated. Tests were made in the Langley 16-foot transonic tunnel and the Langley high speed 7- by 10-foot tunnel for Mach numbers of 0.6, 0.7, and 0.8. Angles of attack investigated were 0 deg, 4 deg, and 8 deg for a range of mass flow ratios. (Author)


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    Title :

    Pressure Distributions for a Rectangular Supersonic Inlet at Subsonic Speeds


    Contributors:

    Publication date :

    1976


    Size :

    478 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English