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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    Titel :

    Pressure Distributions for a Rectangular Supersonic Inlet at Subsonic Speeds


    Beteiligte:
    D. E. Fuller (Autor:in)

    Erscheinungsdatum :

    1976


    Format / Umfang :

    478 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch