Sensitivity analysis on supersonic-boundary-layer stability subject to perturbation of flow parameters

2021 ◽  
Vol 33 (8) ◽  
pp. 084111
Author(s):  
Peixu Guo ◽  
Zhenxun Gao ◽  
Chongwen Jiang ◽  
Chun-Hian Lee
Keyword(s):  
Boundary Layer ◽  
Sensitivity Analysis ◽  
Supersonic Boundary Layer ◽  
Boundary Layer Stability ◽  
Flow Parameters

Influence of coating permeability and roughness on supersonic boundary layer stability

2016 ◽  
Author(s):  
V. I. Lysenko ◽  
S. A. Gaponov ◽  
B. V. Smorodsky ◽  
Yu. G. Yermolaev ◽  
A. D. Kosinov ◽  
...  
Keyword(s):  
Boundary Layer ◽  
Supersonic Boundary Layer ◽  
Boundary Layer Stability

Influence The Direction Of Blowing Gas Through A Porous Surface On The Stability Of The Supersonic Boundary Layer

2015 ◽  
Vol 10 (2) ◽  
pp. 18-26
Author(s):  
Sergey Gaponov ◽  
Aleksandr Semenov
Keyword(s):  
Boundary Layer ◽  
Classical Method ◽  
Supersonic Boundary Layer ◽  
Porous Surface ◽  
Boundary Layer Stability ◽  
Injection Angle ◽  
Plane Plate ◽  
The Stability ◽  
Gas Blowing ◽  
Elementary Waves

In the paper the influence of the gas blowing direction through a porous surface on the supersonic boundary layer stability is investigated theoretically, using the classical method of elementary waves and the evolutionary method at Mach number M = 2. It was found that with decreasing of the gas injection angle to the plane plate the boundary layer stability was improved and the tangential blowing effect on the boundary layer stability is little in a comparison with the case of a boundary layer without mass exchange.

Combined influence of coating permeability and roughness on supersonic boundary layer stability and transition

2016 ◽  
Vol 798 ◽  
pp. 751-773 ◽  
Author(s):  
V. I. Lysenko ◽  
S. A. Gaponov ◽  
B. V. Smorodsky ◽  
Yu. G. Yermolaev ◽  
A. D. Kosinov ◽  
...  
Keyword(s):  
Boundary Layer ◽  
Plate Boundary ◽  
Leading Edge ◽  
Quantitative Agreement ◽  
Supersonic Boundary Layer ◽  
Linear Stability Theory ◽  
Porous Coating ◽  
Boundary Layer Stability ◽  
Turbulent Transition ◽  
Laminar Turbulent Transition

A joint theoretical and experimental investigation of the influence of the surface permeability and roughness on the stability and laminar–turbulent transition of a supersonic flat-plate boundary layer at a free-stream Mach number of $M_{\infty }=2$ has been performed. Good quantitative agreement of the experimental data obtained with artificially generated disturbances performed on models with various porous inserts and calculations based on linear stability theory has been achieved. An increase of the pore size and porous-coating thickness leads to a boundary layer destabilization that accelerates the laminar–turbulent transition. It is shown that as a certain (critical) roughness value is reached, with an increase in the thickness of the rough and porous coating, the boundary layer stability diminishes and the laminar–turbulent transition is displaced towards the leading edge of the model.

The influence of flow parameters on the transition to turbulence in supersonic boundary layer on swept wing

2016 ◽  
Author(s):  
N. V. Semionov ◽  
Yu. G. Yermolaev ◽  
A. D. Kosinov ◽  
A. D. Dryasov ◽  
A. N. Semenov ◽  
...  
Keyword(s):  
Boundary Layer ◽  
Supersonic Boundary Layer ◽  
Transition To Turbulence ◽  
Swept Wing ◽  
Flow Parameters

scholarly journals Experimental Study of the Influence of Unit Reynolds Number on the Laminar-Turbulent Transition on the Model Swept Wing with a Subsonic Leading Edge at M = 2

2021 ◽  
Vol 16 (1) ◽  
pp. 44-52
Author(s):  
Vasilii L. Kocharin ◽  
Nikolai V. Semionov ◽  
Alexander D. Kosinov ◽  
Aleksey A. Yatskikh ◽  
Sofia A. Shipul ◽  
...  
Keyword(s):  
Boundary Layer ◽  
Reynolds Number ◽  
Experimental Studies ◽  
Leading Edge ◽  
Supersonic Boundary Layer ◽  
Swept Wing ◽  
Unit Reynolds Number ◽  
Flow Parameters ◽  
Turbulent Transition ◽  
Laminar Turbulent Transition

Experimental studies of the influence of unit Reynolds number on the laminar-turbulent transition in a supersonic boundary layer of a swept wing with a subsonic leading edge at Mach number 2 are performed. The experiments were performed on a model of a swept wing with a swept angle of the leading edge of 72 degrees and with a 3% profile with a variable chord length in span. The hot-wire measurements showed that a laminar-turbulent transition in a supersonic boundary layer of a swept wing with a subsonic leading edge occurs earlier (~25-30%) than on a model with a supersonic leading edge with the same oncoming flow parameters. It is shown that a change unit Reynolds number insignificant influence the laminar-turbulent transition in the boundary layer of a swept wing with a subsonic leading edge.

Supersonic boundary-layer stability analysis on an aircraft wing

1991 ◽  
Vol 28 (11) ◽  
pp. 721-727 ◽  
Author(s):  
Shreekant Agrawal ◽  
Thomas A. Kinard ◽  
Arthur G. Powell
Keyword(s):  
Boundary Layer ◽  
Stability Analysis ◽  
Supersonic Boundary Layer ◽  
Boundary Layer Stability ◽  
Aircraft Wing
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