scholarly journals Structure of a supersonic separated flow over a compression corner with side walls

2021 ◽  
Author(s):  
V. I. Zapryagaev ◽  
I. N. Kavun ◽  
L. P. Trubitsyna
Keyword(s):  
Separated Flow ◽  
Compression Corner ◽  
Side Walls

FORMATION OF STREAMWISE VORTICES BEHIND THE LINE OF SUPERSONIC SEPARATED FLOW REATTACHMENT AT A COMPRESSION CORNER

2016 ◽  
Vol 47 (3) ◽  
pp. 267-281 ◽  
Author(s):  
Valeriy Ivanovich Zapryagaev ◽  
Ivan Nikolayevich Kavun
Keyword(s):  
Separated Flow ◽  
Streamwise Vortices ◽  
Compression Corner ◽  
Flow Reattachment

scholarly journals Effects of Side Walls on Pipe Inlet Flow (Drag Reduction by Separated Flow Control Using Ring Shaped Small Obstacle)

2009 ◽  
Vol 4 (2) ◽  
pp. 468-478 ◽  
Author(s):  
Toshitake ANDO ◽  
Toshihiko SHAKOUCHI ◽  
Hiroyuki YAMAMOTO ◽  
Koichi TSUJIMOTO
Keyword(s):  
Drag Reduction ◽  
Flow Control ◽  
Separated Flow ◽  
Inlet Flow ◽  
Side Walls ◽  
Flow Drag ◽  
Small Obstacle ◽  
Pipe Inlet

Numerical modeling of the disturbances of the separated flow in a rounded compression corner

2006 ◽  
Vol 41 (4) ◽  
pp. 521-530 ◽  
Author(s):  
I. V. Egorov ◽  
A. V. Novikov ◽  
A. V. Fedorov
Keyword(s):  
Numerical Modeling ◽  
Separated Flow ◽  
Compression Corner

scholarly journals Heat transfer in supersonic separated flow of the compression corner

2019 ◽  
Vol 1382 ◽  
pp. 012049 ◽  
Author(s):  
V I Zapryagaev ◽  
I N Kavun ◽  
L P Trubitsyna
Keyword(s):  
Heat Transfer ◽  
Separated Flow ◽  
Compression Corner

A study of the turbulent separated-flow region occurring at a compression corner in supersonic flow

1965 ◽  
Vol 22 (3) ◽  
pp. 481-505 ◽  
Author(s):  
H. McDonald
Keyword(s):  
Boundary Layer ◽  
Single Layer ◽  
Separated Flow ◽  
Flow Region ◽  
Initial Boundary ◽  
Base Pressure ◽  
Layer Model ◽  
Compression Corner ◽  
Shock Configuration ◽  
Turbulent Separated Flow

The turbulent separated-flow region occurring at a compression corner under certain circumstances at supersonic speed has been examined in the light of recent improvements to base pressure theory (McDonald 1964). This base pressure theory is further extended from what could be termed a single-layer model of the re-attaching boundary layer to a two-layer model, thus enabling the inviscid shock configuration which occurs at the corner to be determined. Application of this analysis to some experimental results indicates a substantial measure of agreement.While this analysis has been framed for estimating the scale of the corner interaction, the extension can of course be applied to increase the range of initial boundary-layer thicknesses to which McDonald's analysis is applicable. An example of such an application is shown to be in good agreement with experiment.

Investigation of supersonic separated flow in a compression corner by laser doppler anemometry

1983 ◽  
Vol 1 (4) ◽  
pp. 195-203 ◽  
Author(s):  
E. C. Baroth ◽  
M. Holt
Keyword(s):  
Laser Doppler Anemometry ◽  
Separated Flow ◽  
Laser Doppler ◽  
Compression Corner

Numerical solutions for high Reynolds number separated flow past a semi-infinite compression corner

1979 ◽  
Vol 7 (3) ◽  
pp. 165-175 ◽  
Author(s):  
M. Napolitano ◽  
M.J. Werle ◽  
R.T. Davis
Keyword(s):  
Reynolds Number ◽  
High Reynolds Number ◽  
Numerical Solutions ◽  
Separated Flow ◽  
Compression Corner ◽  
Flow Past ◽  
High Reynolds

Establishment of steady separated flow over a compression-corner in a free-piston shock tunnel

Shock Waves ◽  
1997 ◽  
Vol 7 (4) ◽  
pp. 249-253 ◽  
Author(s):  
S.G. Mallinson ◽  
S.L. Gai ◽  
N.R. Mudford
Keyword(s):  
Separated Flow ◽  
Shock Tunnel ◽  
Free Piston ◽  
Compression Corner

Stamped Steel Ceilings, Side Walls and Wainscoting

1895 ◽  
Vol 20 (4build) ◽  
pp. 64-64
Keyword(s):  
Side Walls
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