Development of a Ludweig tube with free piston compression heating for scramjet inlet starting experiments

Buttsworth, David R. and Smart, Michael K. (2010). Development of a Ludweig tube with free piston compression heating for scramjet inlet starting experiments. In: 48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition 2010. 48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition, Orlando, Florida, United States, (2010-0588.1-2010-0588.6). 4-7 January 2010.

Author Buttsworth, David R.
Smart, Michael K.
Title of paper Development of a Ludweig tube with free piston compression heating for scramjet inlet starting experiments
Conference name 48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition
Conference location Orlando, Florida, United States
Conference dates 4-7 January 2010
Proceedings title 48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition 2010
Place of Publication Red Hook, NY, United States
Publisher Curran Associates
Publication Year 2010
Sub-type Fully published paper
ISBN 9781617384226
Start page 2010-0588.1
End page 2010-0588.6
Total pages 6
Language eng
Abstract/Summary 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.
Q-Index Code E1
Q-Index Status Provisional Code
Institutional Status UQ

 
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Created: Fri, 25 Mar 2011, 10:19:39 EST by Rose Clements on behalf of School of Mechanical and Mining Engineering