The Hypersonic International Flight Research Experimentation (HIFiRE-5) is a hypersonic flight test vehicle designed to investigate the aerothermodynamics of a three-dimensional geometry. It is a 7-deg minor-axis half-angle elliptic cone with a 2 1 aspect ratio and 2.5 mm nose radius. The flight test occurred in April 2012, but the upper stage of the sounding rocket failed to ignite, resulting in a peak Mach number of about 3 instead of the target of 7. The instrumentation (almost 300 thermocouples and 50 pressure transducers) performed well and provided a wealth of supersonic aeroheating and boundary-layer transition data. The pressure transducers indicated the expected dependence upon angle of attack and yaw and offer a check for the inertial measurement unit. Heat flux was calculated from paired thermocouples and boundary-layer transition locations were identified from the heating rates. Two boundary-layer transition mechanisms were encountered during the supersonic descent. One mode leads to transition over the acreage of the vehicle and correlates well with R e x ; the other mechanism causes the leading-edge boundary-layer transition to advance rapidly over a small range of freestream R e and is suspected to be roughness-induced. The good performance of the instrumentation increases confidence in the success of a repeat flight.


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    Title :

    HIFiRE-5 Flight Test Results


    Contributors:

    Published in:

    Publication date :

    2015-05-01




    Type of media :

    Conference paper , Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English




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