The numerical simulation of turbulent hypersonic flows poses a number of significant challenges. Chief among these challenges is the stringent grid resolution requirement in the boundary layer to accurately predict wall heat ux and skin friction. An enabling modeling concept for such flows is the use of wall models to reduce the near wall compu-tational burden. In this paper, we present the development and validation of a turbulence wall model applicable to high Reynolds number flows. We review modeling choices that arise given a use case of cold-wall hypersonic flow with shock-turbulent boundary layer interaction. Finally, we assess the performance of the model in an a posteriori analysis of a hollow cylinder-are forebody and a large cone-are forebody, and comment on model performance and limitations.
|Original language||English (US)|
|Title of host publication||54th AIAA Aerospace Sciences Meeting|
|Publisher||American Institute of Aeronautics and Astronautics Inc, AIAA|
|State||Published - 2016|
|Event||54th AIAA Aerospace Sciences Meeting, 2016 - San Diego, United States|
Duration: Jan 4 2016 → Jan 8 2016
|Name||54th AIAA Aerospace Sciences Meeting|
|Other||54th AIAA Aerospace Sciences Meeting, 2016|
|Period||1/4/16 → 1/8/16|
Bibliographical noteFunding Information:
The authors would like to acknowledge the efforts of all of the institutions supporting the Air Force Research Laboratory?s Collaborative Center for Aeronautical Sciences, as well as the Boeing Corporation for their support of this work.
© 2016, American Institute of Aeronautics and Astronautics Inc, AIAA . All rights reserved.
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