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An improved flux-split algorithm applied to hypersonic flows in chemical equilibriumAn explicit, finite-difference, shock-capturing numerical algorithm is presented and applied to hypersonic flows assumed to be in thermochemical equilibrium. Real-gas chemistry is either loosely coupled to the gasdynamics by way of a Gibbs free energy minimization package or fully coupled using species mass conservation equations with finite-rate chemical reactions. A scheme is developed that maintains stability in the explicit, finite-rate formulation while allowing relatively high time steps. The codes use flux vector splitting to difference the inviscid fluxes and employ real-gas corrections to viscosity and thermal conductivity. Numerical results are compared against existing ballistic range and flight data. Flows about complex geometries are also computed.
Document ID
19880058827
Document Type
Conference Paper
Authors
Palmer, Grant (NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
August 13, 2013
Publication Date
June 1, 1988
Subject Category
NUMERICAL ANALYSIS
Report/Patent Number
AIAA PAPER 88-2693
Distribution Limits
Public
Copyright
Other