scholarly journals Experimental study of influence of heavy gas injection into boundary layer on perforated model surface at Mach number 2 on its stability to controlled disturbances

2021 ◽  
Author(s):  
V. I. Lysenko ◽  
B. V. Smorodsky ◽  
Yu. G. Ermolaev ◽  
A. D. Kosinov
Keyword(s):  
Boundary Layer ◽  
Experimental Study ◽  
Mach Number ◽  
Gas Injection ◽  
Model Surface ◽  
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.

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 Experimental study of the impact of N-wave on heat transfer in a boundary layer of a flat plate at the Mach number 2

2021 ◽  
Author(s):  
V. L. Kocharin ◽  
A. A. Yatskikh ◽  
D. S. Prishchepova ◽  
A. V. Panina ◽  
Yu. G. Yermolaev ◽  
...  
Keyword(s):  
Heat Transfer ◽  
Boundary Layer ◽  
Experimental Study ◽  
Mach Number ◽  
Flat Plate ◽  
N Wave ◽  
The Impact

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

Experimental Study on Pressure Fluctuations in the Boundary Layer of an Axisymmetric Body

2011 ◽  
Vol 66-68 ◽  
pp. 1488-1493
Author(s):  
Hong Xiao ◽  
Chao Gao ◽  
Zhen Kun Ma
Keyword(s):  
Boundary Layer ◽  
Experimental Study ◽  
Mach Number ◽  
Dynamic Pressure ◽  
Pressure Fluctuations ◽  
Axisymmetric Body ◽  
Pressure Measurements ◽  
Fluctuating Pressure ◽  
Frequency Domains ◽  
Dynamic Pressure Measurements

The characteristics of the fluctuating pressure in the boundary layer of an axisymmetric body have been investigated experimentally using dynamic pressure measurements and Schlieren photograghs. Data were acquired at subsonic and super-sonic Mach numbers. The angles of attack ranged from 0° to 5°. Pressure signals were measured simultaneously in several positions along the model and were analyzed both in the time and frequency domains. The Mach number shows the relevant influence on . Furthermore, the pressure fluctuations’ level decreases with the increasing of Mach number except M=1.15. And it is shown that, the location along the axis of the model and the angles of attack have small effect on pressure fluctuations.

scholarly journals Experimental Study and Application of CFD During the Exploitation Process of Ship in Order to Minimizing the Fuel Consumption

2015 ◽  
Vol 18 (4) ◽  
pp. 136-144
Author(s):  
Quang Le ◽  
Huong Thi Thanh Pham ◽  
He Van Ngo
Keyword(s):  
Boundary Layer ◽  
Experimental Study ◽  
Fuel Consumption ◽  
Water Surface ◽  
Gas Injection ◽  
Ship Hull ◽  
Container Ship ◽  
Air Resistance ◽  
Cfd Method ◽  
Energy Exploitation

The acticle presents a method for minimizing energy exploitation of the ship through reducing ship resistances. Ship resistances include water resistances caused by frictions of water and waves acting on hull part in the water and air resistance acting on the hull part above water surface. To reduce the resistance caused by water friction, the authors proposed a method which intervene directly on the boundary layer of ship hull by the creating a gas injection foaming layer. To reduce air resistance, the authors used CFD method to optimaze arrangement of container on deck for a container ship. Obtained results showed that the proposed method help to save 5-8% of the consuming energy.

scholarly journals About the Relationship between Disturbances in a Free Supersonic Flow and Disturbances in a Boundary Layer at Mach Number 2

2020 ◽  
Vol 15 (2) ◽  
pp. 50-60
Author(s):  
Afanasev ◽  
Kosinov ◽  
Yermolaev ◽  
Semionov
Keyword(s):  
Boundary Layer ◽  
Experimental Study ◽  
Mach Number ◽  
Supersonic Flow ◽  
Flat Plate ◽  
Cross Sections ◽  
Measurement System ◽  
Hot Wire ◽  
Turbulent Transition ◽  
The Relationship

An experimental study of the effect of pulsations of free supersonic flow on the pulsations of the boundary layer of a flat plate with a sharp edge using a new three-channel hot-wire anemometer measurement system is carried out. The spatial-temporal distributions of the correlation coefficient are obtained for the boundary layer cross sections and for the laminar-turbulent transition region.

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