Numerical simulations are performed on a spherical capsule model based on the Orion Crew Exploration Vehicle and compared to experimental data obtained at the Calspan University of Buffalo Research Center. The flow is at Mach 6.4, and a case with an angle of attack of 28 deg is considered. The interest is in predictions of afterbody heating in the presence of massive separation and the resultant highly unsteady wake flow. Detached-eddy simulations of this flowfield are done using several flux schemes, and the effect of mesh refinement is considered. The results are compared to experimental data for mean and fluctuating heat transfer in the separated portion of the afterbody. Comparisons of instantaneous flow features are presented to illustrate varying levels of resolved scales.
Bibliographical noteFunding Information:
This work was sponsored by the U.S. Air Force Office of Scientific Research (AFOSR) 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 AFOSR or the U.S. Government. Previous work and contributions made by Michael D. Barnhardt and discussions with him are gratefully acknowledged.
Copyright © 2014 by Joseph Brock.