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Computation of non-equilibrium hypersonic flow with artificially upstream flux vector splitting (AUFS) schemes.

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Title: Computation of non-equilibrium hypersonic flow with artificially upstream flux vector splitting (AUFS) schemes.
Authors: Tchuen, Ghislain1 tchuengse@yahoo.com, Burtschell, Yves2, Zeitoun, David E.2
Source: International Journal of Computational Fluid Dynamics. Apr2008, Vol. 22 Issue 4, p209-220. 12p. 5 Diagrams, 6 Charts, 14 Graphs.
Subjects: Fluid dynamics, Fluid mechanics, Navier-Stokes equations, Euler characteristic, Viscous flow, Thermodynamics
Abstract: The AUFS scheme has been presented for solving the Euler equations [Sun, M., Takayama, K., 2003. An artificially upstream flux vector splitting scheme for the Euler equations. Journal of Computational Physics, 189, 305-329]. An extension of this high resolution scheme-based on upwind numerical methods has been developed to calculate a two-dimensional hypersonic viscous flowfield in thermochemical non-equilibrium. The time-dependent Navier-Stokes governing equations are computed by using a multi-block finite volume technique on a structured mesh. The convective fluxes at the interfaces are evaluated using a flux vector splitting (FVS) method with a second-order reconstruction of the interface values and the viscous terms are discretised by second-order central differences. A better evaluation of aerodynamic parameters are obtained with this AUFS scheme and they are also compared to those obtained by previous works. The freestream flow conditions of these computations correspond to high-enthalpy flows with a Mach number range between 6.4 and 25.9. The obtained numerical results indicate that the AUFS scheme is accurate, robust, and efficient for the calculation of hypersonic flow. [ABSTRACT FROM AUTHOR]
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Database: Engineering Source
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Abstract:The AUFS scheme has been presented for solving the Euler equations [Sun, M., Takayama, K., 2003. An artificially upstream flux vector splitting scheme for the Euler equations. Journal of Computational Physics, 189, 305-329]. An extension of this high resolution scheme-based on upwind numerical methods has been developed to calculate a two-dimensional hypersonic viscous flowfield in thermochemical non-equilibrium. The time-dependent Navier-Stokes governing equations are computed by using a multi-block finite volume technique on a structured mesh. The convective fluxes at the interfaces are evaluated using a flux vector splitting (FVS) method with a second-order reconstruction of the interface values and the viscous terms are discretised by second-order central differences. A better evaluation of aerodynamic parameters are obtained with this AUFS scheme and they are also compared to those obtained by previous works. The freestream flow conditions of these computations correspond to high-enthalpy flows with a Mach number range between 6.4 and 25.9. The obtained numerical results indicate that the AUFS scheme is accurate, robust, and efficient for the calculation of hypersonic flow. [ABSTRACT FROM AUTHOR]
ISSN:10618562
DOI:10.1080/10618560701766525