Effects of Shock-Tube Cleanliness on Hypersonic Boundary Layer Transition at High Enthalpy
The prediction of a high-speed boundary-layer transition (BLT) location is critical to hypersonic vehicle design; this is because the increased skin friction and surface heating rate after transition result in increased weight of the thermal protection system. Experimental studies using hypervelocity wind tunnels are one component of BLT research.
This material is declared a work of the U.S. Government and is not subject to copyright protection in the United States. Presented as Paper 2015-1786 at the 53rd AIAA Aerospace Sciences Meeting, Kissimmee, FL, 5–9 January 2015; received 17 November 2015; revision received 30 June 2016; accepted for publication 4 July 2016; published online 14 September 2016. This work was an activity that was part of the National Center for Hypersonic Laminar-Turbulent Research, sponsored by the "Integrated Theoretical, Computational, and Experimental Studies for Transition Estimation and Control" project, supported by the U.S. Air Force Office of Scientific Research and NASA (FA9552-09-1-0341). Additionally, this work was part of the "Transition Delay in Hypervelocity Boundary Layers by Means of CO2CO2/Acoustic Interactions" project, sponsored by the U.S. Air Force Office of Scientific Research (FA9550-10-1-0491). J. S. Jewell received additional support from the National Defense Science and Engineering Graduate Fellowship, the Jack Kent Cooke Foundation, and the National Research Council Research Associateship. The authors would like to thank Bahram Valiferdowsi (California Institute of Technology) for help running T5, Ross Wagnild (Sandia National Laboratories) for help with the program to compute the run conditions, and Elizabeth Jewell (University of Michigan) for statistical advice.
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