scholarly journals Evolution of mass flow and total temperature pulsations in flat-plate and swept-wing boundary layers at Mach 2 and 2.5

2020 ◽  
Vol 1677 ◽  
pp. 012033
Author(s):  
A A Yatskikh ◽  
A D Kosinov ◽  
N V Semionov ◽  
Y G Ermolaev ◽  
A V Panina ◽  
...  
Keyword(s):  
Flat Plate ◽  
Boundary Layers ◽  
Mass Flow ◽  
Swept Wing ◽  
Temperature Pulsations ◽  
Total Temperature

scholarly journals The evolution of mass flow and total temperature pulsations in flat plate boundary layer at M=2.5

2017 ◽  
Author(s):  
Aleksey A. Yatskikh ◽  
Gleb L. Kolosov ◽  
Alexander D. Kosinov ◽  
Yury G. Yermolaev ◽  
Nickolay V. Semionov ◽  
...  
Keyword(s):  
Boundary Layer ◽  
Flat Plate ◽  
Mass Flow ◽  
Plate Boundary ◽  
Temperature Pulsations ◽  
Total Temperature ◽  
Flat Plate Boundary Layer

scholarly journals Evolution of localized artificial disturbance in 2D and 3D supersonic boundary layers

2018 ◽  
Vol 234 (1) ◽  
pp. 115-123 ◽  
Author(s):  
Aleksey Yatskikh ◽  
Yury Yermolaev ◽  
Alexander Kosinov ◽  
Nikolai Semionov ◽  
Alexander Semenov
Keyword(s):  
Boundary Layer ◽  
Wave Packet ◽  
Flat Plate ◽  
Boundary Layers ◽  
Plate Boundary ◽  
Hot Wire ◽  
Swept Wing ◽  
Artificial Disturbance ◽  
2D And 3D ◽  
Symmetric Shape

The evolution of a controlled broadband wave packet in flat-plate and swept-wing supersonic boundary layers was experimentally investigated at Mach number M = 2. The wave packet was introduced into the boundary layer by a localized pulse electrical discharge. The structure and evolution downstream of the wave packet were studied by hot-wire measurements. It was found that the wave packet has a symmetric shape in a flat-plate boundary layer, whereas there is asymmetry in case of a swept-wing one. The spectral analysis of the development of different modes of the wave packet was provided.

Transition in the Infinite Swept Attachment Line Boundary Layer

1979 ◽  
Vol 30 (4) ◽  
pp. 607-629 ◽  
Author(s):  
D.I.A. Poll
Keyword(s):  
Boundary Layer ◽  
Pressure Gradient ◽  
Flat Plate ◽  
Boundary Layers ◽  
Free Stream ◽  
Plate Boundary ◽  
Swept Wing ◽  
Civil Aircraft ◽  
Transition Behaviour ◽  
Attachment Line

SummaryThe transition behaviour of the boundary layer which is formed along an infinite swept attachment line has been studied experimentally. Circular trip wires and turbulent flat plate boundary layers have been used as sources of disturbance and the range of parameters covered has been such that the results are directly applicable to full scale flight conditions. Simple criteria have been deduced which allow the state of the boundary layer to be determined for given geometric and free stream properties. Sample calculations for typical swept wing configurations suggest that the majority of civil aircraft will have turbulent attachment lines in the cruise and that subsequent relaminarisation in regions of favourable pressure gradient is unlikely.

Direct total skin-friction measurement of a flat plate in zero-pressure-gradient boundary layers

2009 ◽  
Vol 41 (2) ◽  
pp. 021406 ◽  
Author(s):  
Kiyoto Mori ◽  
Hiroki Imanishi ◽  
Yoshiyuki Tsuji ◽  
Tomohiro Hattori ◽  
Masaharu Matsubara ◽  
...  
Keyword(s):  
Pressure Gradient ◽  
Flat Plate ◽  
Skin Friction ◽  
Boundary Layers ◽  
Friction Measurement

Application of Air Microblowing Through a Porous Wall for Skin Friction Reduction on a Flat Plate

2010 ◽  
Vol 5 (3) ◽  
pp. 38-46
Author(s):  
Vladimir I. Kornilov ◽  
Andrey V. Boiko
Keyword(s):  
Boundary Layer ◽  
Flat Plate ◽  
Skin Friction ◽  
Mass Flow Rate ◽  
Mass Flow ◽  
Flow Rate ◽  
Porous Wall ◽  
Friction Reduction ◽  
Local Skin ◽  
Skin Friction Reduction

The effect of air microblowing through a porous wall on the properties of a turbulent boundary layer formed on a flat plate in an incompressible flow is studied experimentally. The Reynolds number based on the momentum thickness of the boundary layer in front of the porous insert is 3 900. The mass flow rate of the blowing air per unit area was varied within Q = 0−0.0488 кg/s/m2 . A consistent decrease in local skin friction, reaching up to 45−47 %, is observed to occur at the maximal blowing air mass flow rate studied.

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