Abstract
Over the past two decades or so, there have been many advances in the numerical simulation of hypersonic flows, with most effort focused on the development of upwind methods to produce accurate heat transfer rates for steady-state laminar and turbulent flows. With parallelizable implicit methods, it is now possible to obtain full-vehicle solutions at reasonable computational cost. This paper reviews several of the most widely used approaches and discusses how the methods have been tuned to control numerical errors for strongly shocked flows. The paper also discusses recent methods from the incompressible turbulence simulation literature that have been adapted to compressible flows. These methods have dramatically lower levels of numerical dissipation and have been extended to high-order accuracy on smoothly varying hexahedral grids. The increased accuracy of these methods enables the solution of complex physics unsteady hypersonic flows.
| Original language | English (US) |
|---|---|
| Pages (from-to) | 17-28 |
| Number of pages | 12 |
| Journal | Journal of Spacecraft and Rockets |
| Volume | 52 |
| Issue number | 1 |
| DOIs | |
| State | Published - Jan 1 2015 |
Bibliographical note
Funding Information:This work was sponsored by the U.S. Air Force Office of Scientific Research under grants FA9550-10-1-0563 and FA9550-12-1-064 and by the Department of Defense National Security Science and Engineering Faculty Fellowship. The views and conclusions contained herein are those of the author and should not be interpreted as necessarily representing the official policies or endorsements, either expressed or implied, of the U.S. Air Force Office of Scientific Research or the U.S. Government.
Publisher Copyright:
Copyright © 2014 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.