Hypersonic Blunt Body Computations Including Real Gas Effects

Thermochemical nonequilibrium modeling of a low-power argon arcjet wind tunnel

“…(2). We use the Roe scheme, 70 with extension to nonequilibrium real gases 71 and entropy correction, 72 to calculate the inviscid flux F, whose spatial accuracy is extended to the second order using the monotone upstream-centered schemes for conservation laws (MUSCL) 73 with van Albada's limiter. 74 Our numerical test with several inviscid flux schemes revealed the Roe scheme to be most suitable for the present computations, because its low dissipation stabilizes the behavior of the arc plume, and its achievable convergence residual is three orders of magnitude smaller than those of modern advection upstream splitting methods.…”

Numerical simulation of re-entry flow around the Space Shuttle with finite-rate chemistry

“…Klopfer et al 24 presented hypersonic flow calculations around a cylinder, and reported that the cell Reynolds number should be on the order of unity when computing heat transfer results. However, they employed the artificial viscosity on every wave, 25 which degrades the numerical accuracy for heating rates. artificial viscosity makes the cell Reynolds number on the order of 100 to be sufficient for computing heating rates, whereas Klopfer's method requires an even finer grid.…”

A BGK model for high temperature rarefied gas flows

“…When the temperature is larger, chemical reactions occur, and if the flow is in chemical equilibrium, empirically tabulated laws can be used to compute all the thermodynamical quantities (pressure, entropy, temperature, specific heats) in terms of density and internal energy, like the one given in [1,16]. These laws give a closure of the compressible Navier-Stokes equations, that are used for simulations in the continuous regime, at moderate to low altitudes (see, for example, [24]).…”