Other
Scientific paper
Feb 2005
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2005esasp.563..541w&link_type=abstract
Proceedings of the Fifth European Symposium on Aerothermodynamics for Space Vehicles (ESA SP-563). 8-11 November 2004, Cologne,
Other
Scientific paper
A gun tunnel has been converted to run as a direct-connect facility for supersonic combustion experiments. To achieve the required stagnation temperature of 1800K, a flammable mixture was added to the barrel that ignited during the shock compression process. The advantage of this method is that the test gas has a much smaller fraction of water vapour than conventional vitiated facilities, since shock compression alone can raise the stagnation temperature to 900K. The test time of 20ms is an order of magnitude longer than a conventional shock tunnel due to the fact that the pressure waves that terminate the test, travel in the cold driver gas behind the piston. The tunnel is run at high pressure to provide sufficient air mass for the duration of the test. A throttle placed between the end of the barrel and the entrance to the supersonic nozzle reduces stagnation pressure to the appropriate level for the combustor. A hydrogen fueled combustor tested in this facility demonstrated an oscillatory supersonic combustion. Wall static pressure measurements showed the development of a strong pressure rise at the rear of the combustor that was observed to move upstream into the isolator. Once this occurred, pressure at the front of the combustor dropped and that at the rear began to rise again until once again the wave moved upstream and into the isolator. Three cycles of this oscillatory combustion process were observed before the end of the test. The combination of cold walls allowing high frequency measurement and a relatively long test time provided a clear advantage over shock-tunnels or vitiated facilities when observing this unsteady combustion process.
Cain T. M.
Walton Chelsea
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