For flight at high Mach numbers, thermal and chemical nonequilibrium may exist in the mean flow and thus affect the stability of the flow. A computational tool was developed to analyze a hypersonic mean flow and its stability including thermochemical nonequilibrium. The mean flow analysis employs the Navier-Stokes equations with a translational/vibrational temperature model for thermal nonequilibrium and a five species reacting air model for chemical nonequilibrium. The stability analysis employs linear stability theory to describe the spatial amplification of two and three-dimensional disturbances. The computational tool is used to determine the frequency and spatial amplification of disturbances which may lead to boundary layer transition on cold wall and adiabatic flat plates. The effect of thermal and chemical nonequilibrium on stability is shown to depend on the disturbance mode.
|Original language||English (US)|
|State||Published - 1996|
|Event||34th Aerospace Sciences Meeting and Exhibit, 1996 - Reno, United States|
Duration: Jan 15 1996 → Jan 18 1996
|Other||34th Aerospace Sciences Meeting and Exhibit, 1996|
|Period||1/15/96 → 1/18/96|
Bibliographical noteFunding Information:
Support for this work was provided by NASA under Grant No. NAGW-1331 to the Mars Mission Research Center at North Carolina State University. Ms. Hudson received support from Sandia National Laboratories, Albuquerque, New Mexico. Allocation grants from the North Carolina Supercomputing Center and the Minnesota Supercomputer Institute at the University of Minnesotaprovided time on a Cray Y-MP and Cray C-90 respectively.