Temperature measurements were obtained on the Pegasus booster from launch through Mach 8.0. The majority of sensors were thin-foil temperature gages installed near the surface within the vehicle's ablating thermal protection system. These gages were distributed on the wing surfaces and on the wing-body fairing or fillet. Temperature time histories from these installations are presented. In addition, thermocouples were installed on the surface of nonablating plugs located on the fairing. These sensors were more responsive to changes in flight conditions than the foil gages and allowed a derivation of convective heat flux. A heating rate magnification of 2 was found in the vicinity of the wing shock interaction.


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    Title :

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


    Contributors:

    Publication date :

    1991-12-01


    Type of media :

    Conference paper


    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 First Flight of the Pegasus Air-Launched Space Booster

    G. K. Noffz / R. E. Curry / E. A. Haering et al. | NTIS | 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