Journal
JOURNAL OF SPACECRAFT AND ROCKETS
Volume 52, Issue 3, Pages 650-663Publisher
AMER INST AERONAUTICS ASTRONAUTICS
DOI: 10.2514/1.A33142
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- U.S. Air Force Research Laboratory
- Australian Defence Science and Technology Organisation [AF-06-0046]
- Douglas Dolvin, AFRL/RQHV
- John Schmisseur, formerly Air Force Office of Scientific Research and currently University of Tennessee Space Institute
- Rengasamy Ponnappan, AFOSR/RTA
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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 2.5mm nose radius. The flight test occurred in April2012, 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 Re-x; the other mechanism causes the leading-edge boundary-layer transition to advance rapidly over a small range of freestream Re 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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