University of Minnesota
Aerospace Engineering and Mechanics
Fall 1999 Seminar Series

DNS and LES Closure of Reacting Turbulence in Hypersonic Flows

Dr. Pino Martin

Department of Aerospace Engineering and Mechanics, University of Minnesota


The boundary layers that are formed on hypersonic vehicles are very hot, chemically reacting, and turbulent. Currently it is not feasible to make accurate numerical simulations of these flows because of their complexity. Therefore, the boundary layer on realistic hypersonic vehicles is simulated either assuming that the boundary layers are laminar, or using simple models that have not been calibrated for hypersonic applications. The large eddy simulation technique has recently become a promising tool for the detailed computation of combustion flows. The aim of the research presented here is to develop methods for large-eddy simulations of reacting, turbulent, hypersonic flows. To complete this task, we need a clear understanding of the fundamental flows of interest, as well as a complete closure of the large-eddy simulation equations. In the current research, the results from the direct numerical simulation of reacting isotropic turbulence and reacting, hypersonic, turbulent boundary layers are analyzed. In this way, a basic understanding of the physical mechanisms that govern the turbulence-chemistry interaction has been developed. Furthermore, the direct numerical simulation database has been used to develop and test models for the unclosed terms in the large-eddy simulation equations.

Friday, October 29, 1999
209 Akerman Hall
2:30-3:30 p.m.

Refreshments served after the seminar in 227 Akerman Hall.
Disability accomodations provided upon request.
Contact Kristal Belisle, Senior Secretary, 625-8000.