Hypersonic Shock Interactions about a 25 Deg/65 Deg Sharp Double Cone

by National Aeronautics and Space Administration

This paper presents the results of a numerical study of shock interactions resulting from Mach 10 air flow about a sharp double cone. Computations are made with the direct simulation Monte Carlo (DSMC) method by using two different codes: the G2 code of Bird and the DAC (DSMC Analysis Code) code of LeBeau. The flow conditions are the pretest nominal free-stream conditions specified for the ONERA R5Ch low-density wind tunnel. The focus is on the sensitivity of the interactions to grid resolution while providing information concerning the flow structure and surface results for the extent of separation, heating, pressure, and skin friction. Moss, James N. and LeBeau, Gerald J. and Glass, Christopher E. Johnson Space Center; Langley Research Center NASA/TM-2002-211778, L-18199, NAS 1.15:211778

28 pages, Paperback

Published June 19, 2018

About the author

The National Aeronautics and Space Administration (NASA) is an independent agency of the U.S. federal government responsible for the civil space program, aeronautics research, and space research.