Two normal -wedge-inlet configurations (straight and sweptback splitter plates) were investigated in the Lewis 8- by 6-foot supersonic wind tunnel at Mach numbers of 1.50 to 1.99. Negligible differences occurred in the performances of the two normal-wedge inlets. In comparison with a previously tested scoop inlet, the normal-wedge configuration showed superior thrust-minus-drag characteristics at Mach 1.99. However the scoop inlet was better at Mach numbers of 1.80 and 1.50.


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    Titel :

    Investigation of an Underslung Normal-wedge Inlet at Free-stream Mach Numbers from 1.50 to 1.99


    Beteiligte:

    Erscheinungsdatum :

    19.03.1957


    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch




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