POST Flight Analysis of the Hyshot Supersonic Combustion Flight Experiment in Heg

Details POST Flight Analysis of the Hyshot Supersonic Combustion Flight Experiment in Heg POST Flight Analysis of the Hyshot Supersonic Combustion Flight Experiment in Heg

Feb 2005

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2005esasp.563..535g&link_type=abstract

Proceedings of the Fifth European Symposium on Aerothermodynamics for Space Vehicles (ESA SP-563). 8-11 November 2004, Cologne,

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The first phase of the HyShot supersonic combustion ramjet (scramjet) flight experiment program of The University of Queensland in Australia was designed to provide benchmark data on supersonic combustion for a flight Mach number of approximately M=8. Two flights (HyShot I and II) have so far been undertaken from the Woomera Prohibited Area in Australia. The first flight was undertaken on October 30th 2001 and the second on July 30th 2002. While the first flight was unsuccessful at delivering the experiment to its planned trajectory, the second flight was succesful and supersonic combustion was observed along the specified trajectory range. The operating range of the High Enthalpy Shock Tunnel G¨ottingen (HEG) of the German Aerospace Center (DLR) was recently extended. The facility has now the capability of testing a complete scramjet engine with internal combustion and external aero-dynamics at M=7.8 flight conditions in altitudes of about 30 km. A post flight analysis of the HyShot flight experiment was performed using an operational scramjet wind tunnel model with a geometry which is identical to that of the flight configuration. This test campaign included detailed wall pressure and heat transfer measurements for M=7.8 flight conditions in an altitude range between 27 km and 33 km.

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