Inserting a splitter plate in the subsonic diffuser caused a pressure-recovery loss of about 1 percent for an inlet with a long nearly constant-area throat section. The loss was due to the increased surface area. Another inlet, which had a comparatively rapid area increase immediately after the throat, experienced pressure-recovery losses of 5 and 6 percent at Mach numbers of 1.8 and 2.0, respectively, and about 1 percent at Mach 1.5.


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    Titel :

    Preliminary Investigation of Effect on Performance of Dividing Conical-spike Nose Inlets into Halves at Mach Numbers 1.5 to 2.0


    Beteiligte:
    Allen, John L (Autor:in)

    Erscheinungsdatum :

    19.12.1955


    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch