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)


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

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


    Contributors:

    Publication date :

    1975


    Size :

    98 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English