Development of a Ludwieg tube with free piston compression heating for scramjet inlet starting experiments
Paper
Paper/Presentation Title | Development of a Ludwieg tube with free piston compression heating for scramjet inlet starting experiments |
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Presentation Type | Paper |
Authors | Buttsworth, David R. (Author) and Smart, Michael K. (Author) |
Journal or Proceedings Title | Proceedings of the 48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition (AIAA 2010) |
Number of Pages | 6 |
Year | 2010 |
Place of Publication | Reston, VA. United States |
ISBN | 9781600867392 |
Web Address (URL) of Paper | http://pdf.aiaa.org/preview/2010/CDReadyMASM10_1812/PV2010_588.pdf |
Conference/Event | 48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition (AIAA 2010) |
Event Details | 48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition (AIAA 2010) Event Date 04 to end of 07 Jan 2010 Event Location Orlando, United States |
Abstract | A Ludwieg tube facility with free piston compression heating has been developed at the University of Southern Queensland for scramjet inlet starting experiments. The Ludwieg tube facility generates a steady flow for about 200 ms which is sufficient for the inlet starting experiments, but the impulsive starting of the hypersonic flow generated by the Ludwieg tube facility can aid inlet starting. For definitive confirmation of inlet start-ability, we have established the essential hardware for pneumatically unstarting the inlet after a steady hypersonic flow is generated in the facility. The pneumatic flow blockage can then be removed to determine whether the inlet will restart under steady in-flow conditions. A Rectangular-to-Elliptical Shape Transition (REST) inlet design has been developed for Mach 8 flight. Preliminary experiments with the REST inlet positioned at the exit of the Mach 6 nozzle have therefore been performed. Pressure measurements and schlieren visualization are used to investigate the flow characteristics within the inlet. Results indicate that the inlet self-starts with the facility, but flow in the inlet changes during the nominally steady run period produced by the Ludwieg tube facility even without attempting to pneumatically unstart the inlet. These changes are attributed to an increase in the test section background pressure which drives compression waves into the Mach 6 free jet flow captured by the inlet. Future effort will be directed towards ensuring Mach 6 free jet compression effects do not affect the scramjet inlet flow. |
Keywords | background pressure; compression effects; compression heating; compression waves; elliptical shapes; flow blockage; flow characteristic; flow condition; free jets; free piston; inlet design; ludwieg tube; Queensland; Schlieren visualization; scramjet inlets; test sections; unstart |
ANZSRC Field of Research 2020 | 400105. Flight dynamics |
400106. Hypersonic propulsion and hypersonic aerothermodynamics | |
401706. Numerical modelling and mechanical characterisation | |
Public Notes | Files associated with this item cannot be displayed due to copyright restrictions. |
Byline Affiliations | Computational Engineering and Science Research Centre |
University of Queensland | |
Institution of Origin | University of Southern Queensland |
https://research.usq.edu.au/item/q0x64/development-of-a-ludwieg-tube-with-free-piston-compression-heating-for-scramjet-inlet-starting-experiments
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