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Published June 2010 | Published
Book Section - Chapter Open

Effect of Concave Wall Geometry on Heat Transfer in Hypersonic Boundary Layers


Heat transfer measurements are made to investigate the effects of concave surface curvature on a high-stagnation enthalpy boundary layer in a Mach 5.1 flow. Experiments are carried out using two curved models with 16 and 25 degree turning angles, and baseline planar models (at plate and linear ramp) for comparative study. Streamwise and spanwise cross-sections are obtained. Significant destabilization of the boundary layer is observed over the adverse pressure gradient geometries. For the curved surfaces, the heat flux distribution appears to exhibit a quadratic dependence with streamwise distance, in contrast with the linear dependence observed on the linear ramp.

Additional Information

© 2010 by University of Illinois. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission. AIAA 2010-4986. This work was funded through the Air Force Office of Scientific Research FA9550-08-1-0172 with Dr. John Schmisseur as program manager. We are grateful to the Caltech T5 group, Prof. Hans Hornung, Bahram Valiferdowski, Drs Eric Marineau, Adam Rasheed, and Ivett Leyva for their help with thermocouples. The authors would like to thank Ryan Fontaine, Manu Sharma, and Andy Swantek for their help with this work.

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