@Article{Santos:2006:EfCoAe,
author = "Santos, Wilson Fernando Nogueira",
affiliation = "{Instituto Nacional de Pesquisas Espaciais}",
title = "Effects of compressibility on aerodynamic surface quantities over
low-density hypersonic wedge flow",
journal = "Journal of the Brazilian Society of Mechanical Sciences and
Engineering",
year = "2006",
volume = "28",
number = "3",
pages = "362--372",
month = "Jul.-Sept.",
keywords = "Rarefied flow, hypersonic flow, DSMC, blunt leading edge,
stagnation point heatung.",
abstract = "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.",
issn = "0100-7386",
language = "en",
targetfile = "effects.pdf",
urlaccessdate = "08 maio 2024"
}