The Wind-US flow solver has been modified to include real gas thermodynamic properties and real gas fluxes of conserved variables. The real gas evaluations relevant to a specific molecule have been isolated to a single subroutine so that any substances can be implemented relatively easily. Molecular nitrogen and hydrogen have been implemented in the program to date. The real gas model has been implemented in the Wind-US Roe approximate Riemann solver at this time. The real gas nitrogen model has been used to predict converging-diverging nozzle flow at total pressures ranging from nominally 250 to 20,000 psi at a nominal stagnation temperature of 3000 o R and exit Mach numbers of 8 to 14. A comparison of the 20,000-psi results with data is presented in this paper. The real gas hydrogen model is used to model high-pressure shock tube calculations relevant to analysis of light gas hypervelocity gun range facilities. * The research reported herein was performed by the Arnold Engineering Development Center (AEDC), Air Force Materiel Command. Work and analysis for this research were performed by personnel of Aerospace Testing Alliance, the operations, maintenance, information management, and support contractor for AEDC. Further reproduction is authorized to satisfy needs of the U. S. Government. † Senior Member, AIAA. ‡ Associate Fellow, AIAA.
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