24th Congress of International Council of the Aeronautical Sciences, 29 August-3, September 2004, Yokohama, Japan
Paper ICAS 2004-3.7.R.1

NUMERICAL PREDICTION OF STAGNATION-POINT SHOCK-DETACHMENT DISTANCE FOR HYPERSONIC LOW DENSITY FLOW OVER BLUNT NOSE SHAPES

W. F. N. Santos
Combustion and Propulsion Laboratory National Institute for Space Research Cachoeira Paulista, SP 12630-000, Brazil

Keywords: hypersonic flow, rarefied flow, dsmc, blunt leading edge, shock standoff distance

Computations using the DSMC method are presented for hypersonic flow over flat-nose leading edges. The primary aim of this paper is to examine the geometry effect of such leading edges on the shock wave structure.

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