A survey of temperature measurements at speeds through Mach 8.0 on the first flight of the Pegasus air-launched booster system is discussed. In addition, heating rates were derived from the temperature data obtained on the fuselage in the vicinity of the wing shock interaction. Sensors were distributed on the wing surfaces, leading edge, and on the wing-body fairing or fillet. Side-by-side evaluations were obtained for a variety of sensor installations. Details of the trajectory reconstruction through first-stage separation are provided. Given here are indepth descriptions of the sensor installations, temperature measurements, and derived heating rates along with interpretations of the results.


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    Title :

    Aerothermal Test Results from the First Flight of the Pegasus Air-Launched Space Booster


    Contributors:
    G. K. Noffz (author) / R. E. Curry (author) / E. A. Haering (author) / P. Kolodziej (author)

    Publication date :

    1991


    Size :

    53 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    Aerothermal test results from the first flight of the Pegasus air-launched space booster

    Noffz, Gregory K. / Curry, Robert E. / Haering, Edward A., Jr. et al. | NTRS | 1991




    Aerothermal Test Results from the Second Flight of the Pegasus Booster

    G. K. Noffz / T. R. Moes / E. A. Haering et al. | NTIS | 1992


    Pegasus Air-Launched Space Booster Flight Test Program

    A. L. Elias / M. A. Knutson | NTIS | 1995