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Journal of the Brazilian Society of Mechanical Sciences and Engineering

versão impressa ISSN 1678-5878versão On-line ISSN 1806-3691

Resumo

SANTOS, Wilson F. N.. Effects of compressibility on aerodynamic surface quantities over low-density hypersonic wedge flow. J. Braz. Soc. Mech. Sci. & Eng. [online]. 2006, vol.28, n.3, pp.362-372. ISSN 1678-5878.  http://dx.doi.org/10.1590/S1678-58782006000300015.

Hypersonic flow past truncated wedges at zero incidence in thermal non-equilibrium is investigated for a range of Mach number from 5 to 12. The simulations were performed by using a Direct Simulation Monte Carlo (DSMC) Method. The study focuses the attention of designers of hypersonic configurations on the fundamental parameter of bluntness, which can have an important impact on even initial design. Some significant differences between sharp and blunt leading edges were noted on the heat transfer, pressure and skin friction coefficients as well as on total drag. Interesting features observed in the surface fluxes showed that small leading edge thickness compared to the freestream mean free path still has important effects on high Mach number leading edge flows. The numerical results present reasonable comparison for wall pressure and heat transfer predictions with experiments conducted in a shock tunnel.

Palavras-chave : Rarefied flow; hypersonic flow; DSMC; blunt leading edge; stagnation point heating.

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