Numerical simulation of the generation mechanism of axisymmetric supersonic jet screech tones

In this paper, the discrete-time complex dynamical networks with dynamic weighted value of connection relationships are regarded to be composed of the node and link subsystems, and the state variables of the two subsystems are mutually coupled. Different from most of the existing researches on synchronization or stabilization of nodes, the emphasis of this paper is on the links instead of nodes. This paper mainly focuses on the generation mechanism of structural balance in the link subsystem, the nodes only play an auxiliary role. Associated with the dynamic coupling term in the link subsystem, the suitable controller is proposed for node subsystem such that the structural balance of link subsystem without control input be achieved indirectly. Finally, a numerical simulation is given to show the effectiveness of the method in this paper.

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Numerical Simulation of Axisymmetric Jet Screech Tones Using a General Purpose Finite-Volume CFD Code

48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition ◽

10.2514/6.2010-272 ◽

2010 ◽

Cited By ~ 1

Author(s):

Konstantin Kurbatskii

Keyword(s):

Numerical Simulation ◽

Finite Volume ◽

General Purpose ◽

Axisymmetric Jet ◽

Screech Tones

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Experimental Investigation on Supersonic Jet Screech Tones

Applied Mechanics and Materials ◽

10.4028/www.scientific.net/amm.232.213 ◽

2012 ◽

Vol 232 ◽

pp. 213-217

Author(s):

Jia Ming Li ◽

Chun Bo Hu ◽

Jun Hua Bai

Keyword(s):

Mach Number ◽

Field Distribution ◽

Experimental Measurement ◽

Supersonic Jet ◽

Jet Noise ◽

Occurrence Frequency ◽

Supersonic Jet Noise ◽

Nozzle Size ◽

Screech Tones ◽

Peak Value

In order to investigate the characteristic of the supersonic jet screech tones, an experimental bench of the supersonic jet was designed and a free field noise signal acquisition system was established. Effects of the nozzle size and jet Mach number on jet noise sound field distribution was analyzed, through the result comparison of supersonic jet noise experimental measurement. Results indicate that the field distribution of supersonic jet screech tones is characterized with very strong directivity. Peak value of the screech tones decrease and occurrence frequency of the screech tones increase with the decreasing jet exit Mach number; occurrence frequency of the screech tones decrease with the increasing nozzle size, but the peak value change very less. The experimental measurement of supersonic jet noise provides mechanism research of sound production with data supports and references; and also provides the numerical modeling of supersonic jet noise with validation criteria.

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Numerical Simulation of Supersonic Jet Control by Tabs with Slanted Perforation

International Journal of Turbo and Jet Engines ◽

10.1515/tjj-2019-0015 ◽

2019 ◽

Vol 0 (0) ◽

Author(s):

G. Ezhilmaran ◽

Suresh Chandra Khandai ◽

Yogesh Kumar Sinha ◽

S. Thanigaiarasu

Keyword(s):

Numerical Simulation ◽

Mach Number ◽

Near Field ◽

Pressure Ratio ◽

Supersonic Jet ◽

Pressure Gradients ◽

Nozzle Pressure Ratio ◽

Nozzle Pressure ◽

Jet Control ◽

Different Diameters

Abstract This paper presents the numerical simulation of Mach 1.5 supersonic jet with perforated tabs. The jet with straight perforation tab was compared with jets having slanted perforated tabs of different diameters. The perforation angles were kept as 0° and 10° with respect to the axis of the nozzle. The blockage areas of the tabs were 4.9 %, 4.9 % and 2.4 % for straight perforation, 10° slanted perforation ( {{{\Phi }}_{\ }} = 1.3 mm) and 10° slanted perforation ( {{{\Phi }}_{\ }} = 1.65 mm) respectively. The 3-D numerical simulations were carried out using the software. The mixing enhancements caused by these tabs were studied in the presence of adverse and favourable pressure gradients, corresponding to nozzle pressure ratio (NPR) of 3, 3.7 and 5. For Mach number 1.5 jet, NPR 3 corresponds to 18.92 % adverse pressure gradients and NPR 5 corresponds to 35.13 % favourable pressure gradients. The centerline Mach number of the jet with slanted perforations is found to decay at a faster rate than uncontrolled nozzle and jet with straight perforation tab. Mach number plots were obtained at both near-field and far field downstream locations. There is 25 % and 65 % reduction in jet core length were observed for the 0° and 10° perforated tabs respectively in comparison to uncontrolled jet.

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Numerical Simulation of the Viscous Flow for the Supersonic Jet Element

Advanced Materials Research ◽

10.4028/www.scientific.net/amr.189-193.2362 ◽

2011 ◽

Vol 189-193 ◽

pp. 2362-2365

Author(s):

Yong Yu ◽

Guo Qing Zhang ◽

Fei Wang

Keyword(s):

Experimental Data ◽

Numerical Simulation ◽

Unsteady Flow ◽

Viscous Flow ◽

Steady Flow ◽

Supersonic Jet ◽

Calculated Data ◽

Numerical Precision ◽

Good Agreement

The viscous flow of the supersonic jet element was simulated numerically based on CFD technology, and many tests have been done to verify the numerical precision. The results show that the calculated data are good agreement with the experimental data. So the numerical simulation of the viscous flow for the supersonic jet element is accurate and reliable, and it can be applied to investigate the steady flow and unsteady flow in supersonic jet element.

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