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

Laminar Supersonic Boundary Layer Of The Binary Gas Mixture

2016 ◽  
Vol 11 (1) ◽  
pp. 5-15
Author(s):  
Sergey Gaponov ◽  
Boris Smorodsky
Keyword(s):  
Boundary Layer ◽  
Gas Injection ◽  
Plate Boundary ◽  
Supersonic Boundary Layer ◽  
Model Surface ◽  
Transfer Coefficients ◽  
Molecular Weights ◽  
Boundary Layer Equations ◽  
Binary Gas Mixture ◽  
Heavy Gas

Theoretical investigation of the properties of a compressible binary-mixture boundary-layer in the framework of local self-similar boundary-layer equations. We have considered the problem, when the foreign gas of various molecular weights – lighter and heavier than air – has been injected into the flat-plate boundary-layer through the permeable model surface. Computations of the binarymixture velocity, density and temperature profiles as well as foreign gas concentration in such boundary layers at different Mach numbers have been performed. It has been found that increase of a foreign gas injection leads to a monotonous decrease of the skin friction and heat transfer coefficients. It has been established that at free stream Mach number M‹2 action of a heavy gas injection from the model surface into the boundary layer is similar to the action of the model cooling. This injection increases the density of the mixture near the wall. As a result, the profiles of the supersonic boundary layer are modified in such a way that the boundary-layer linear stability should be increased with injection of a foreign gas with high molecular weight. This in turn should lead to a shift in position of the laminar-turbulent transition downstream.

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

Investigation of the effect of heavy gas injection into a supersonic boundary layer on laminar-turbulent transition

2017 ◽  
Vol 52 (6) ◽  
pp. 769-776 ◽  
Author(s):  
S. A. Gaponov ◽  
Yu. G. Ermolaev ◽  
N. N. Zubkov ◽  
A. D. Kosinov ◽  
V. I. Lysenko ◽  
...  
Keyword(s):  
Boundary Layer ◽  
Gas Injection ◽  
Supersonic Boundary Layer ◽  
Turbulent Transition ◽  
Heavy Gas ◽  
Laminar Turbulent Transition

Stability of supersonic boundary layer under the influence of heavy gas injection: experimental study

2018 ◽  
Vol 25 (2) ◽  
pp. 183-190 ◽  
Author(s):  
V. I. Lysenko ◽  
B. V. Smorodsky ◽  
Yu. G. Ermolaev ◽  
A. D. Kosinov
Keyword(s):  
Boundary Layer ◽  
Experimental Study ◽  
Gas Injection ◽  
Supersonic Boundary Layer ◽  
Heavy Gas

scholarly journals Influence of Heavy Gas Blowing into the Wall Layer of Supersonic Boundary-Layer on Its Transition

2017 ◽  
Vol 12 (1) ◽  
pp. 50-56 ◽  
Author(s):  
V. I. Lysenko ◽  
◽  
B. V. Smorodsky ◽  
Yu. G. Ermolaev ◽  
S. A. Gaponov ◽  
...  
Keyword(s):  
Boundary Layer ◽  
Wall Layer ◽  
Supersonic Boundary Layer ◽  
Heavy Gas ◽  
Gas Blowing

The Combined Influence Of Heat And Mass Transfer Through A Porous Wall On The Boundary Layer Stability Compressible Gas At High Mach Numbers

2015 ◽  
Vol 10 (3) ◽  
pp. 31-40
Author(s):  
Sergey Gaponov ◽  
Natalya Terekhova
Keyword(s):  
Boundary Layer ◽  
Mass Transfer ◽  
Heat And Mass Transfer ◽  
Porous Wall ◽  
Supersonic Boundary Layer ◽  
Management Regime ◽  
High Mach ◽  
Heavy Gas ◽  
Gas Blowing ◽  
Compressible Gas

This work continues the research on modeling the management regime in the boundary layer of compressible gas. The effect of the distribution of heat and mass transfer on the stability characteristics of supersonic boundary layer at high supersonic Mach number M = 5,35. The focus is on the modeling of acoustic disturbances in the conditions as a normal injection, in which the only nonzero component of the average velocity V, and the injection of other areas, including tangential, when the wall is not zero only U component. Production close to the problem of influence on the development of gas curtain small oscillations. It is assumed that the effect of injection of a homogeneous gas of different temperature similar to that of the blowing gas of different density, namely, blowing cold gas simulates heavy gas blowing and vice versa. Therefore in this modeling work is achieved by changing the factor of temperature (heating or cooling of the walls). The variant when the socalled regime implemented «lock» when the velocity perturbations on the porous surface can be taken as zero.

scholarly journals Influence of Dispersed Tangential Heavy-Gas Blowing into the Supersonic Boundary-Layer on Its Stability

2018 ◽  
Vol 13 (1) ◽  
pp. 25-32
Author(s):  
V. I. Lysenko ◽  
◽  
S. A. Gaponov ◽  
N. N. Zubkov ◽  
B. V. Smorodsky ◽  
...  
Keyword(s):  
Boundary Layer ◽  
Supersonic Boundary Layer ◽  
Heavy Gas ◽  
Gas Blowing

Influence Of Heavy Gas Blowing Into The Wall Layer Of Supersonic Boundary-Layer On Its Transition

2017 ◽  
Vol 12 (1) ◽  
pp. 50-56
Author(s):  
Vladimir Lysenko ◽  
Boris Smorodsky ◽  
Yuri Yermolaev ◽  
Sergey Gaponov ◽  
Aleksandr Kosinov ◽  
...  
Keyword(s):  
Boundary Layer ◽  
Sulfur Hexafluoride ◽  
Plate Boundary ◽  
Leading Edge ◽  
Wall Layer ◽  
Supersonic Boundary Layer ◽  
Turbulent Transition ◽  
Heavy Gas ◽  
Gas Blowing ◽  
Laminar Turbulent Transition

The experimental investigation of the influence of the distributed blowing of heavy gas (sulfur hexafluoride of SF6) into the wall layer of supersonic flat-plate boundary layer (at free-stream Mach number M = 2) on the laminar-turbulent transition have been performed. For the first time experimentally it is shown that in case of such blowing there is a boundary-layer stabilization, and the laminar-turbulent transition is removed from the model leading edge.

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