Influence of distributed heavy-gas injection on stability and transition of supersonic boundary-layer flow

2019 ◽  
Vol 31 (10) ◽  
pp. 104103 ◽  
Author(s):  
V. I. Lysenko ◽  
S. A. Gaponov ◽  
B. V. Smorodsky ◽  
Y. G. Yermolaev ◽  
A. D. Kosinov
Keyword(s):  
Boundary Layer ◽  
Boundary Layer Flow ◽  
Gas Injection ◽  
Supersonic Boundary Layer ◽  
Layer Flow ◽  
Heavy Gas

Influence of heavy-gas injection into supersonic boundary layer on its stability to controlled disturbances

2019 ◽  
Author(s):  
Vladimir I. Lysenko ◽  
Boris V. Smorodsky ◽  
Yuri G. Ermolaev ◽  
Alexander D. Kosinov
Keyword(s):  
Boundary Layer ◽  
Gas Injection ◽  
Supersonic Boundary Layer ◽  
Heavy Gas

An instability in supersonic boundary-layer flow over a compression ramp

1995 ◽  
Vol 300 ◽  
pp. 265-285 ◽  
Author(s):  
K. W. Cassel ◽  
A. I. Ruban ◽  
J. D. A. Walker
Keyword(s):  
Boundary Layer ◽  
Boundary Layer Flow ◽  
Streamwise Velocity ◽  
Supersonic Boundary Layer ◽  
Recirculation Region ◽  
Hypersonic Boundary Layer ◽  
Recirculating Flow ◽  
Inflection Points ◽  
Compression Ramp ◽  
Layer Flow

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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