An experimental investigation of the nozzle roughness effect on streamwise vortices in a supersonic jet

1997 ◽  
Vol 38 (1) ◽  
pp. 78-86 ◽  
Author(s):  
V. I. Zapryagaev ◽  
A. V. Solotchin
Keyword(s):  
Experimental Investigation ◽  
Supersonic Jet ◽  
Streamwise Vortices ◽  
Roughness Effect

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.

Experimental Investigation of the Nozzle Roughness Effect on the Flow Parameters in the Mixing Layer of an Axisymmetric Subsonic High-Velocity Jet

2020 ◽  
Vol 55 (2) ◽  
pp. 185-193
Author(s):  
D. A. Gubanov ◽  
A. A. Dyad’kin ◽  
V. I. Zapryagaev ◽  
I. N. Kavun ◽  
S. P. Rybak
Keyword(s):  
Experimental Investigation ◽  
High Velocity ◽  
Mixing Layer ◽  
Roughness Effect ◽  
Flow Parameters

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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