Experimental investigation of a supersonic Mach 2.5 wall jet in a hypersonic Mach 6 crossflow: Sharp leading edge flat plate with laminar incoming boundary layer

被引：0
|
作者：
Santarelli, P [1 ]
Charbonnier, JM [1 ]
Leblanc, R [1 ]
机构：
[1] Von Karman Inst Fluid Dynam, Aeronaut Aerosp Dept, B-1640 Rhode St Genese, Belgium
来源：
FOURTH INTERNATIONAL SYMPOSIUM ON EXPERIMENTAL AND COMPUTATIONAL AEROTHERMODYNAMICS OF INTERNAL FLOWS, VOL II, PROCEEDINGS | 1999年
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中图分类号：
V [航空、航天];
学科分类号：
08 ; 0825 ;
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页码：156 / 163
页数：8
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