Pressure and heat transfer tests were conducted simulating flight conditions which the space shuttle external tank will experience prior to break-up. The tests were conducted in the Calspan 48-inch Hypersonic Shock Tunnel and simulated entry conditions for nominal, abort-once-around (AOA), and return to launch site (RTLS) launch occurrences. Surface pressure and heat-transfer-rate distributions were obtained with and without various protuberences (or exterior hardware) on the model at Mach numbers from 15.2 to 17.7 at angles of attack from -15 deg to -180 deg and at several roll angles. The tests were conducted over a Reynolds number range from 1300 to 58,000, based on model length. (Author)


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    Titel :

    An Experimental Investigation of the NASA Space Shuttle External Tank at Hypersonic Mach Numbers


    Beteiligte:
    C. E. Wittliff (Autor:in)

    Erscheinungsdatum :

    1975


    Format / Umfang :

    98 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch