A primary factor governing hypersonic flowfield characteristics of blunt vehicles entering planetary atmospheres is the normal shock density ratio. Hence, a means of duplicating or simulating the high density ratios experienced during planetary entry is needed. One facility having the capability of generating a range of hypersonic-hypervelocity flow conditions in arbitrary test gases is the expansion tube. Preliminary shock shape results obtained in the Langley 6-in. expansion tube at hypersonic conditions are presented. Normal shock density ratios from approximately 4 to 19 were generated using helium, air, and CO2 test gases at freestream velocities from 5 to 7 km/sec. Test models were a flat-faced cylinder and the Viking aeroshell.


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    Titel :

    Shock shapes of blunt bodies in hypersonic helium, air, and CO2 flows


    Beteiligte:
    Miller, C. G. (Autor:in) / Moore, J. A. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    1974-03-01


    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Shock Shapes of Blunt Bodies in Hypersonic Helium, Air, and CO, Flows

    CHARLES G. MILLER AND JOHN A. MOORE | AIAA | 1974


    Shock Standoff on Hypersonic Blunt Bodies in Nonequilibrium Gas Flows

    George R. Inger / Charlotte Higgins / Richard Morgan | AIAA | 2002


    Shock standoff on hypersonic blunt bodies in nonequilibrium gas flows

    Inger, George / Higgins, Charlotte / Morgan, Richard | AIAA | 2001