An experimental investigation of the flow dynamics of streamwise vortices of various strengths interacting with a supersonic jet

2014 ◽  
Vol 26 (8) ◽  
pp. 086102 ◽  
Author(s):  
N. Heeb ◽  
E. Gutmark ◽  
K. Kailasanath
Keyword(s):  
Experimental Investigation ◽  
Supersonic Jet ◽  
Flow Dynamics ◽  
Streamwise Vortices

Experimental investigation of the flow dynamics of rheologically complex fluids in a Maxblend impeller system using PIV

2013 ◽  
Vol 91 (1) ◽  
pp. 7-17 ◽  
Author(s):  
A. Fontaine ◽  
Y. Guntzburger ◽  
F. Bertrand ◽  
L. Fradette ◽  
M.-C. Heuzey
Keyword(s):  
Experimental Investigation ◽  
Complex Fluids ◽  
Flow Dynamics

Flow dynamics and enhanced mixing in a converging–diverging channel

2016 ◽  
Vol 807 ◽  
pp. 167-204 ◽  
Author(s):  
S. W. Gepner ◽  
J. M. Floryan
Keyword(s):  
Three Dimensional ◽  
Travelling Wave ◽  
Flow Dynamics ◽  
Streamwise Vortices ◽  
Dimensional Model ◽  
Three Dimensional Model ◽  
Wave Instability ◽  
Unsteady Separation ◽  
Flow Stabilization ◽  
Diverging Channel

An analysis of flows in converging–diverging channels has been carried out with the primary goal of identifying geometries which result in increased mixing. The model geometry consists of a channel whose walls are fitted with spanwise grooves of moderate amplitudes (up to 10 % of the mean channel opening) and of sinusoidal shape. The groove systems on each wall are shifted by half of a wavelength with respect to each other, resulting in the formation of a converging–diverging conduit. The analysis is carried out up to Reynolds numbers resulting in the formation of secondary states. The first part of the analysis is based on a two-dimensional model and demonstrates that increasing the corrugation wavelength results in the appearance of an unsteady separation whose onset correlates with the onset of the travelling wave instability. The second part of the analysis is based on a three-dimensional model and demonstrates that the flow dynamics is dominated by the centrifugal instability over a large range of geometric parameters, resulting in the formation of streamwise vortices. It is shown that the onset of the vortices may lead to the elimination of the unsteady separation. The critical Reynolds number for the vortex onset initially decreases as the corrugation amplitude increases but an excessive increase leads to the stream lift up, reduction of the centrifugal forces and flow stabilization. The flow dynamics under such conditions is again dominated by the travelling wave instability. Conditions leading to the formation of streamwise vortices without interference from the travelling wave instability have been identified. The structure and the mixing properties of the saturated states are discussed.

Flow Stucture of Supersonic Underexpanded Jet With Microjets Injection

2013 ◽  
Vol 8 (1) ◽  
pp. 44-55
Author(s):  
Dmitriy Gubanov ◽  
Valeriy Zapryagaev ◽  
Nikolay Kiselev
Keyword(s):  
Flow Structure ◽  
Numerical Study ◽  
Mixing Layer ◽  
Supersonic Jet ◽  
Wave Structure ◽  
Streamwise Vortices ◽  
Jet Mixing ◽  
Underexpanded Jet ◽  
Supersonic Underexpanded Jet ◽  
The Impact

Experimental and numerical study of transversal microjets injection influence on the supersonic underexpanded jet flow structure has been performed. Data of measurements and calculation have acceptable agreement. Interaction of microjets with main supersonic jet sets to a decrease of an initial gasdynamic region. Microjets lead to a longitudinal streamwise vortices generation and a mushroom-like flow structures create on an external jet mixing layer. Dissipation of longitudinal streamwise vortices was observed at the second jet cell. Complex gasdynamic flow structure of the supersonic underexpanded jet interacting with supersonic microjets has been studied for the first time. This structure contains system of complex chock waves and expansion waves spreading from the position of the impact microjets/main jet localization place. Future of interaction process a chock-wave structure of main jet with additional shock waves has been studied

Experimental Investigation of Nozzle Exit Reflector Effect on Supersonic Jet

Shock Waves ◽  
2006 ◽  
Vol 15 (3-4) ◽  
pp. 229-239 ◽  
Author(s):  
Y.-H. Kweon ◽  
Y. Miyazato ◽  
T. Aoki ◽  
H.-D. Kim ◽  
T. Setoguchi
Keyword(s):  
Experimental Investigation ◽  
Nozzle Exit ◽  
Supersonic Jet

An Experimental Investigation on Transpiration Cooling for Supersonic Vehicle Nose Cone Using Porous Material

2014 ◽  
Vol 541-542 ◽  
pp. 690-694 ◽  
Author(s):  
Lian Jin Zhao ◽  
Jia Lin ◽  
Jian Hua Wang ◽  
Jin Long Peng ◽  
De Jun Qu ◽  
...  
Keyword(s):  
Experimental Investigation ◽  
Porous Material ◽  
Supersonic Jet ◽  
Leading Edge ◽  
Injection System ◽  
Aerodynamic Heating ◽  
Hypersonic Vehicles ◽  
Transpiration Cooling ◽  
Cone Model ◽  
Nose Cone

During hypersonic flight or cruise in the near space, the aerodynamic heating causes a very high temperature on the leading edge of hypersonic vehicles. Transpiration cooling has been recognized the most effective cooling technology. This paper presents an experimental investigation on transpiration cooling using liquid water as coolant for a nose cone model of hypersonic vehicles. The nose cone model consists of sintered porous material. The experiments were carried out in the Supersonic Jet Arc-heated Facility (SJAF) of China Academy of Aerospace Aerodynamics (CAAA) in Beijing. The cooling effect in the different regions of the model was analyzed, and the shock wave was exhibited. The pressure variations of the coolant injection system were continuously recorded. The aim of this work is to provide a relatively useful reference for the designers of coolant driving system in practical hypersonic vehicles.

An Experimental Investigation of Streamwise Vortices in the Wake of a Bluff Body

1994 ◽  
Vol 8 (6) ◽  
pp. 621-625 ◽  
Author(s):  
J. Wu ◽  
J. Sheridan ◽  
J. Soria ◽  
M.C. Welsh
Keyword(s):  
Experimental Investigation ◽  
Bluff Body ◽  
Streamwise Vortices
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