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- W2292783013 abstract "Hypersonic vehicles experience difierent ∞ow regimes during ∞ight due to changes in atmospheric density. Computational Fluid Dynamics (CFD), while relatively computationally inexpensive, is not physically accurate in areas of highly non-equilibrium ∞ows. The direct simulation Monte Carlo (DSMC) method, while physically accurate for all ∞ow regimes, is relatively computationally expensive. In a continuing efiort to understand the performance of CFD and DSMC in hypersonic ∞ows, the current study investigates the efiect of continuum breakdown on surface aerothermodynamic properties (pressure, shear stress and heat transfer rate) of a cylinder in Mach 10 and Mach 25 ∞ows of argon gas for several difierent ∞ow regimes, from the continuum to a rarefled gas. Several difierent velocity slip and temperature jump boundary conditions are examined for use with the CFD method. CFD and DSMC solutions are obtained at each condition. Total drag and peak heat transfer rate predictions by CFD remains within about 6% of the DSMC predictions ∞ ¶!" @default.
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- W2292783013 date "2007-01-01" @default.
- W2292783013 modified "2023-09-24" @default.
- W2292783013 title "Velocity Slip and Temperature Jump in Hypersonic" @default.
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