%0 Journal Article
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%@nexthigherunit 8JMKD3MGPCW/3ET38CH
%@archivingpolicy denypublisher denyfinaldraft
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%3 effects.pdf
%@dissemination WEBSCI; PORTALCAPES.
%2 sid.inpe.br/mtc-m17@80/2006/08.28.17.01.01
%4 sid.inpe.br/mtc-m17@80/2006/08.28.17.00
%X 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.
%8 Jul.-Sept.
%N 3
%T Effects of compressibility on aerodynamic surface quantities over low-density hypersonic wedge flow
%K Rarefied flow, hypersonic flow, DSMC, blunt leading edge, stagnation point heatung.
%@secondarytype PRE PI
%@group LCP-INPE-MCT-BR
%@secondarykey INPE--PRE/
%@issn 0100-7386
%@affiliation Instituto Nacional de Pesquisas Espaciais
%B Journal of the Brazilian Society of Mechanical Sciences and Engineering
%P 362-372
%D 2006
%V 28
%A Santos, Wilson Fernando Nogueira,
%@area COMB