Heat Transfer on a Double Wedge Geometry in Hypervelocity Air and Nitrogen Flows

Creators: Swantek, A. B.; Austin, J. M.

Abstract

We investigate shock wave/boundary-layer interaction and resulting heat transfer in hypervelocity double wedge flows. An expansion tube is used to generate air and nitrogen flows with stagnation enthalpies ranging from 2.1-8.0 MJ/kg and Mach numbers from 4-7. The range of free stream conditions were selected to investigate the impact of thermochemical effects by i) systematically varying the chemical composition from nitrogen to air while maintaining constant the stagnation enthalpy or the Mach number, and ii) varying the stagnation enthalpy. Flow features are visualized with schlieren photography, and heat transfer is measured using fast response coaxial thermocouples. Data are presented for both nitrogen and air test conditions with eight cases in total. Current results indicate significantly different behavior in flows with enthalpies as low as 4 MJ/kg between air and nitrogen test conditions.

Additional Information

© 2012 by Andrew B Swantek. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission. AIAA 2012-0284. This work was funded through the U.S. Air Force Office of Scientific Research (award FA 9550-11-1-0129) with Dr. John Schmisseur as program manager. Invaluable assistance with thermocouple instrumentation and data processing was provided by William Flaherty at Illinois. We are very grateful to Prof. Hans Hornung and the Caltech T5 group for the generous sharing of their thermocouple design and expertise.

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