Detailed analysis of a hybrid CFD-DSMC method for hypersonic non-equilibrium flows

Research output: Chapter in Book/Report/Conference proceedingConference contribution

3 Scopus citations

Abstract

A hybrid numerical scheme designed for hypersonic non-equilibrium flows is presented which solves the Navier-Stokes equations in regions of near-equilibrium and uses the direct simulation Monte Carlo method where the flow is in non-equilibrium. Detailed analysis of each stage of the hybrid cycle illustrates the difficulty in defining physically correct DSMC boundary conditions in regards to both macroscopic state, and velocity distribution. However, results also show that DSMC boundary conditions have little effect on a previously initialized interior particle domain. A sub-relaxation technique capable of determining macroscopic, hydrodynamic properties in a DSMC simulation is used to determine low-scatter boundary conditions for the NS domain. Particle and continuum domains adapt during the hybrid simulation through application of a continuum breakdown parameter based on the gradient-length Knudsen number. The hybrid code reproduces experimental results and full DSMC simulations in half the time for a large range of 1D shock waves in argon and diatomic nitrogen gas.

Original languageEnglish (US)
Title of host publication38th AIAA Thermophysics Conference
PublisherAmerican Institute of Aeronautics and Astronautics Inc.
ISBN (Print)9781624100611
DOIs
StatePublished - 2005
Externally publishedYes
Event38th AIAA Thermophysics Conference - Toronto, ON, Canada
Duration: Jun 6 2005Jun 9 2005

Publication series

Name38th AIAA Thermophysics Conference

Other

Other38th AIAA Thermophysics Conference
CountryCanada
CityToronto, ON
Period6/6/056/9/05

Bibliographical note

Funding Information:
This work is sponsored by the Space Vehicle Transportation Institute, under NASA Grant NCC3-989 with joint sponsorship from the Department of Defense.

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