AN INSTABILITY IN SUPERSONIC BOUNDARY-LAYER FLOW OVER A COMPRESSION RAMP

被引:30
作者
CASSEL, KW [1 ]
RUBAN, AI [1 ]
WALKER, JDA [1 ]
机构
[1] CENT AEROHYDRODYNAM INST,ZHUKOVSKII,RUSSIA
关键词
D O I
10.1017/S0022112095003685
中图分类号
O3 [力学];
学科分类号
08 ; 0801 ;
摘要
Separation of a supersonic boundary layer (or equivalently a hypersonic boundary layer in a region of weak global interaction) near a compression ramp is considered for moderate wall temperatures. For small ramp angles, the flow in the vicinity of the ramp is described by the classical supersonic triple-deck structure governing a local viscous-inviscid interaction. The boundary layer is known to exhibit recirculating flow near the corner once the ramp angle exceeds a certain critical value. Here it is shown that above a second and larger critical ramp angle, the boundary-layer flow develops an instability. The instability appears to be associated with the occurrence of inflection points in the streamwise velocity profiles within the recirculation region and develops as a wave packet which remains stationary near the corner and grows in amplitude with time.
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收藏
页码:265 / 285
页数:21
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