A critical component in optimizing hypersonic vehicle design and performance is to accurately predict the thermal response of the vehicle. In order to efficiently simulate the aerothermal interactions, a fully coupled conjugate heat transfer solver was developed. The simulations were performed with US3D, an implicit finite-volume unstructured compressible flow solver, with a newly developed implicit finite-volume unstructured heat conduction solver. The grids for the fluid and solid are non-face-matched due to the different grid requirements for fluid and solid. Results are shown for a simple two-dimensional cylinder test case, in order to analyze the accuracy of the face-matched vs. non-face-matched grids. Two and three-dimensional simulations are presented for a rectangular hypersonic inlet-isolator geometry. As expected, results show the heating of the solid in the isolator region is lower at the shock-wave boundary layer interaction locations when compared to the surrounding area.
|Original language||English (US)|
|Title of host publication||23rd AIAA Computational Fluid Dynamics Conference, 2017|
|Publisher||American Institute of Aeronautics and Astronautics Inc, AIAA|
|State||Published - 2017|
|Event||23rd AIAA Computational Fluid Dynamics Conference, 2017 - Denver, United States|
Duration: Jun 5 2017 → Jun 9 2017
|Name||23rd AIAA Computational Fluid Dynamics Conference, 2017|
|Other||23rd AIAA Computational Fluid Dynamics Conference, 2017|
|Period||6/5/17 → 6/9/17|
Bibliographical notePublisher Copyright:
© 2017, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.