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Journal articles on the topic 'Supersonic Axisymmetric Jet'

Author: Grafiati

Published: 4 June 2021

Last updated: 7 September 2023

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1

Samanta, Arnab. "On the axisymmetric stability of heated supersonic round jets." Proceedings of the Royal Society A: Mathematical, Physical and Engineering Sciences 472, no. 2188 (2016): 20150817. http://dx.doi.org/10.1098/rspa.2015.0817.

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We perform an inviscid, spatial stability analysis of supersonic, heated round jets with the mean properties assumed uniform on either side of the jet shear layer, modelled here via a cylindrical vortex sheet. Apart from the hydrodynamic Kelvin–Helmholtz (K–H) wave, the spatial growth rates of the acoustically coupled supersonic and subsonic instability waves are computed for axisymmetric conditions ( m =0) to analyse their role on the jet stability, under increased heating and compressibility. With the ambient stationary, supersonic instability waves may exist for any jet Mach number M j ≥2,

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2

Peters, Ivo R., Yoshiyuki Tagawa, Nikolai Oudalov, et al. "Highly focused supersonic microjets: numerical simulations." Journal of Fluid Mechanics 719 (February 19, 2013): 587–605. http://dx.doi.org/10.1017/jfm.2013.26.

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AbstractBy focusing a laser pulse inside a capillary partially filled with liquid, a vapour bubble is created that emits a pressure wave. This pressure wave travels through the liquid and creates a fast, focused axisymmetric microjet when it is reflected at the meniscus. We numerically investigate the formation of this microjet using axisymmetric boundary integral simulations, where we model the pressure wave as a pressure pulse applied on the bubble. We find a good agreement between the simulations and experimental results in terms of the time evolution of the jet and on all parameters that c

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3

Zapryagaev, V. I., N. P. Kiselev, and A. A. Pivovarov. "Gasdynamic structure of an axisymmetric supersonic underexpanded jet." Fluid Dynamics 50, no. 1 (2015): 87–97. http://dx.doi.org/10.1134/s001546281501010x.

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4

Tipnis, T. J., M. V. Finnis, K. Knowles, and D. Bray. "Density measurements for rectangular free jets using background-oriented schlieren." Aeronautical Journal 117, no. 1194 (2013): 771–85. http://dx.doi.org/10.1017/s0001924000008447.

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AbstractAn experimental study incorporating the use of the Background-Oriented Schlieren (BOS) technique was performed to measure the density field of a rectangular supersonic jet. This technique is easier to set up than conventional schlieren since the optical alignment involving the various mirrors, lenses and knife-edge is replaced by a background pattern and a single digital camera. The acquired images which contain information of density gradients in the flow are solved as a Poisson equation and further processed using deconvolution and tomographic algorithms to generate a 3D domain which

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5

MATÉ, B., I. A. GRAUR, T. ELIZAROVA, et al. "Experimental and numerical investigation of an axisymmetric supersonic jet." Journal of Fluid Mechanics 426 (January 10, 2001): 177–97. http://dx.doi.org/10.1017/s0022112000002329.

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A comprehensive study of a steady axisymmetric supersonic jet of CO2, including experiment, theory, and numerical calculation, is presented. The experimental part, based on high-sensitivity Raman spectroscopy mapping, provides absolute density and rotational temperature maps covering the significant regions of the jet: the zone of silence, barrel shock, Mach disk, and subsonic region beyond the Mach disk. The interpretation is based on the quasi-gasdynamic (QGD) system of equations, and its generalization (QGDR) considering the translational–rotational breakdown of thermal equilibrium. QGD and

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6

Kitazono, Kazumasa, Hiroshi Fukuoka, Nao Kuniyoshi, et al. "Study of Interaction between Unsteady Supersonic Jet and Vortex Rings Discharged from Elliptical Cell." Materials Science Forum 910 (January 2018): 137–42. http://dx.doi.org/10.4028/www.scientific.net/msf.910.137.

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Pulsed laser ablation with an elliptical cell gives well-defined thermodynamic conditions to the growth of high-quality thin films. The unsteady supersonic jet formed by the shock tube with small high-pressure chamber was used as a simple alternative model of pulsed laser ablation. The vortex ring formed by the shock wave is important to reveal behavior of unsteady supersonic jet discharged from elliptical cell. However, there has been little effort to investigate the interaction between the vortex ring and the jet. The purpose of the present study is to investigate the behavior of the vortex

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7

Dahl, Milo D., and Philip J. Morris. "Supersonic Jet Noise Reductions Predicted With Increased Jet Spreading Rate." Journal of Fluids Engineering 120, no. 3 (1998): 471–76. http://dx.doi.org/10.1115/1.2820686.

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In this paper, predictions are made of noise radiation from single, supersonic, axisymmetric jets. We examine the effects of changes in operating conditions and the effects of simulated enhanced mixing that would increase the spreading rate of the jet shear layer on radiated noise levels. The radiated noise in the downstream direction is dominated by mixing noise and, at higher speeds, it is well described by the instability wave noise radiation model. Further analysis with the model shows a relationship between changes in spreading rate due to enhanced mixing and changes in the far field radi

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8

Graham, Mary Jane, and Paul Weinacht. "Numerical Investigation of Supersonic Jet Interaction for Axisymmetric Bodies." Journal of Spacecraft and Rockets 37, no. 5 (2000): 675–83. http://dx.doi.org/10.2514/2.3617.

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9

Mironov, Sergey, Vladimir Aniskin, Tatiana Korotaeva, and Ivan Tsyryulnikov. "Effect of the Pitot Tube on Measurements in Supersonic Axisymmetric Underexpanded Microjets." Micromachines 10, no. 4 (2019): 235. http://dx.doi.org/10.3390/mi10040235.

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This paper describes the results of methodical investigations of the effect of the Pitot tube on measurements of gas-dynamic parameters of supersonic axisymmetric underexpanded real and model microjets. Particular attention is paid to distortions of Pitot pressure variations on the jet axis associated with the wave structure of the jet and to distortions of the supersonic core length. In experiments with model jets escaping from nozzles with diameters ranging from 0.52 to 1.06 mm into the low-pressure chamber, the measurements are performed by the Pitot tubes 0.05 to 2 mm in diameter. The resu

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10

Zamuraev, Vladimir, and Anna Kalinina. "Creating Of Stable Transonic Zone Into Supersonic Flow In Axisymmetrical Channel By The Action Of Jet And Energy Sources." Siberian Journal of Physics 11, no. 4 (2016): 45–51. http://dx.doi.org/10.54362/1818-7919-2016-11-4-45-51.

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The effect of the jet flowing out from the gas generator through a narrow annular gap, on the shockwave structure of the flow in the axisymmetric channel of variable section is studied. The effect of the gap size is investigated. The possibility to control the shock-wave structure of supersonic flow in the channel and creating of transonic area using pulsed-periodic energy supply and jet is studied.

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11

Lee, Incheol, and Duck Joo Lee. "Investigation on the Source Locations of Axisymmetric Screech Tones Utilizing Data from Numerical Simulation." Journal of Theoretical and Computational Acoustics 27, no. 04 (2019): 1850058. http://dx.doi.org/10.1142/s2591728518500585.

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The source locations of axisymmetric modes of screech tones are numerically investigated. Fourth-order optimized compact scheme and fourth-order Runge–Kutta method are used to solve the 2-D axisymmetric Euler equations. The screech tone is successfully reproduced, and the change in wavelength with respect to jet Mach number shows good agreement with the experimental data. At various low supersonic jet Mach numbers, the time-averaged contours of Mach number and root-mean-square pressure are investigated to identify the location of maximum interaction between shock cell structures and vortices.

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12

Caraballo, E., M. Samimy, J. Scott, S. Narayanan, and J. DeBonis. "Application of Proper Orthogonal Decomposition to a Supersonic Axisymmetric Jet." AIAA Journal 41, no. 5 (2003): 866–77. http://dx.doi.org/10.2514/2.2022.

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13

SUZUKI, Hiromasa, Masaki ENDO, and Yoko SAKAKIBARA. "1410 A study on supersonic jet issuing from axisymmetric nozzle." Proceedings of the Fluids engineering conference 2014 (2014): _1410–1_—_1410–2_. http://dx.doi.org/10.1299/jsmefed.2014._1410-1_.

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14

Rossi, P., G. Bodo, S. Massaglia, A. Ferrari, and A. Malagoli. "3-D Simulations of Kelvin-Helmholtz Instabilities in Supersonic Jets." Symposium - International Astronomical Union 175 (1996): 453–54. http://dx.doi.org/10.1017/s0074180900081432.

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One of the key processes governing the structure and evolution of astrophysical jets is their interaction with the surrounding medium. A jet can deposit momentum and energy in the ambient medium, and entrain external material. The main physical process responsible for mixing between a jet flow and the ambient medium is the Kelvin-Helmholtz (KH) instability. We have previously analysed the 2D evolution of the axisymmetric modes of a cylindrical jet (Bodo et al 1994) and of the antisymmetric modes of a planar slab jet (Bodo et al 1995). These last are thought to give indications of the 3D evolut

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15

Bogey, Christophe, and Romain Gojon. "Feedback loop and upwind-propagating waves in ideally expanded supersonic impinging round jets." Journal of Fluid Mechanics 823 (June 22, 2017): 562–91. http://dx.doi.org/10.1017/jfm.2017.334.

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The aeroacoustic feedback loop establishing in a supersonic round jet impinging on a flat plate normally has been investigated by combining compressible large-eddy simulations and modelling of that loop. At the exit of a straight pipe nozzle of radius $r_{0}$, the jet is ideally expanded, and has a Mach number of 1.5 and a Reynolds number of $6\times 10^{4}$. Four distances between the nozzle exit and the flat plate, equal to $6r_{0}$, $8r_{0}$, $10r_{0}$ and $12r_{0}$, have been considered. In this way, the variations of the convection velocity of the shear-layer turbulent structures accordin

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16

SAMIMY, M., J. H. KIM, M. KEARNEY-FISCHER, and A. SINHA. "Acoustic and flow fields of an excited high Reynolds number axisymmetric supersonic jet." Journal of Fluid Mechanics 656 (June 14, 2010): 507–29. http://dx.doi.org/10.1017/s0022112010001357.

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An axisymmetric perfectly expanded Mach 1.3 jet, with a Reynolds number based on the nozzle exit diameter (ReD) of 1.1 × 106 and turbulent boundary layer at the nozzle exit, was excited using localized arc filament plasma actuators over a wide range of forcing Strouhal numbers (StDF). Eight actuators distributed azimuthally were used to excite azimuthal modes m = 0–3. Far-field acoustic, flow velocity and irrotational near-field pressure were probed with a three-fold objective: (i) to investigate the broadband far-field noise amplification reported in the literature at lower speeds and ReD usi

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17

Mitchell, Brian E., Sanjiva K. Lele, and Parviz Moin. "Direct Computation of Mach Wave Radiation in an Axisymmetric Supersonic Jet." AIAA Journal 35, no. 10 (1997): 1574–80. http://dx.doi.org/10.2514/2.15.

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18

Krothapalli, Anjaneyulu, James McDaniel, and Donald Baganoff. "Effect of slotting on the noise of an axisymmetric supersonic jet." AIAA Journal 28, no. 12 (1990): 2136–38. http://dx.doi.org/10.2514/3.10534.

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19

Fourguette, D. C., M. G. Mungal, and R. W. Dibble. "Time evolution of the shear layer of a supersonic axisymmetric jet." AIAA Journal 29, no. 7 (1991): 1123–30. http://dx.doi.org/10.2514/3.10712.

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20

Kuehner, Joel P., Blake B. Anderson, Jonathan G. Flittner, and J. Craig Dutton. "Characteristics of a Central Bleed Jet in Supersonic Axisymmetric Base Flow." Journal of Spacecraft and Rockets 44, no. 2 (2007): 347–54. http://dx.doi.org/10.2514/1.24838.

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21

Mitchell, Brian E., Sanjiva K. Lele, and Parviz Moin. "Direct computation of Mach wave radiation in an axisymmetric supersonic jet." AIAA Journal 35 (January 1997): 1574–80. http://dx.doi.org/10.2514/3.13714.

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22

K., Sathish Kumar, and Senthilkumar Chidambaram. "Supersonic jet flow control using semi-circular corrugated tabs." Aircraft Engineering and Aerospace Technology 91, no. 10 (2019): 1340–52. http://dx.doi.org/10.1108/aeat-01-2019-0021.

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Purpose The purpose of this study is to increase the jet mixing effectiveness of Mach 1.6 axisymmetric jet using semi-circular corrugated triangular tabs (Tabs A, B and C), in which the locations of the semi-circular corrugations are varied along the leaned sides of the triangular tabs. Design/methodology/approach The tabs are fixed at the exit of the nozzle facing each other 180° apart. To quantify the jet mixing effectiveness of the semi-circular corrugated tabs, Pitot pressure measurements were carried out for the cases of over-expansion, marginally over-expansion and under-expansion levels

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23

Zhong, Jian-lin, Jie Ren, and Da-wei Ma. "Thermoelasticity Coupling Transient Response of Composite-Material Direction Pipe." Shock and Vibration 2018 (November 15, 2018): 1–10. http://dx.doi.org/10.1155/2018/6937372.

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Based on the positive scheme method, the thermal load of the jet flow in an inner composite-material direction pipe is obtained, and the thermoelasticity coupling transient response is investigated. The positive scheme method with second-order accuracy is extended for solving the axisymmetric Euler equations, and the supersonic axisymmetric jet flow over a missile afterbody containing jet exhaust is simulated. The correctness of the development for the positive scheme method is verified. With the developed positive scheme method used to simulate the jet flow in the inner direction pipe, the th

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24

Zapryagaev, Valeriy, Ivan Kavun, and Nikolay Kiselev. "Flow Feature in Supersonic Non-Isobaric Jet near the Nozzle Edge." Aerospace 9, no. 7 (2022): 379. http://dx.doi.org/10.3390/aerospace9070379.

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Using the example of studying the supersonic underexpanded jet initial section, the issue of interpreting the experimental visualization data and Pitot pressure measurement data using the results of numerical calculations (2d RANS k-ω SST) is discussed. It is shown that the gradient S-shaped feature of the gas-dynamic structure near the nozzle exit, observed in the form of a barrel shock, is a characteristic that separates the expansion and compression regions, and downstream is transformed into a barrel shock. It has been established that the reason for the observed S-shaped curvature of this

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25

KROTHAPALLI, A., E. RAJKUPERAN, F. ALVI, and L. LOURENCO. "Flow field and noise characteristics of a supersonic impinging jet." Journal of Fluid Mechanics 392 (August 10, 1999): 155–81. http://dx.doi.org/10.1017/s0022112099005406.

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This paper describes the results of a study examining the flow and acoustic characteristics of an axisymmetric supersonic jet issuing from a sonic and a Mach 1.5 converging–diverging (C–D) nozzle and impinging on a ground plane. Emphasis is placed on the Mach 1.5 nozzle with the sonic nozzle used mainly for comparison. A large-diameter circular plate was attached at the nozzle exit to measure the forces generated on the plate owing to jet impingement. The experimental results described in this paper include lift loss, particle image velocimetry (PIV) and acoustic measurements. Suckdown forces

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26

Hussain, G. Fayaaz, Afthab Shaban Nasser, Mohammad Mohiudeen Nawaz, Bikash Kumar Mondal, and N. Karthikeyan. "Effect of Perforated Tabs on the Noise Field of an Axisymmetric Jet." Applied Mechanics and Materials 307 (February 2013): 250–56. http://dx.doi.org/10.4028/www.scientific.net/amm.307.250.

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Effect of triangular tabs with circular perforations on the acoustic far-field of an axisymmetric jet issued from a convergent nozzle of exit diameter of 30.16 mm was studied for both subsonic and sonic underexpanded cases. It was found that the noise in the low frequency range (Strouhal number < 0.29) reduced in both subsonic and supersonic jet mach numbers with a penalty in high frequency noise. OASPL plots showed that overall noise levels in subsonic jets increased due to the introduction of tabs except for far downstream angles where the noise levels reduced by 2 dB. Overall noise level

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27

Karthikeyan, N., and B. T. N. Sridhar. "Numerical and Experimental Studies on the Supersonic Coaxial Jet Mixing." Advanced Materials Research 354-355 (October 2011): 691–95. http://dx.doi.org/10.4028/www.scientific.net/amr.354-355.691.

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Coaxial nozzles are an integral part of many engineering systems where mixing of different fluid streams is required. Single noncircular nozzles have been shown to have better mixing characteristics than their axisymmetric counterparts. Therefore, a combination of such nozzles into coaxial configurations is promising. The aim of the present study is to quantitatively determine the effects of the geometry of the primary supersonic jet on the mixing characteristics with the secondary high speed subsonic jet. Measurements of pressure profiles at several positions along central axis of jets using

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28

Zhang, Tian, Deji Jing, Shaocheng Ge, Jiren Wang, Xiangxi Meng, and ShuaiShuai Ren. "Numerical simulation of the dimensional transformation of atomization in a supersonic aerodynamic atomization dust-removing nozzle based on transonic speed compressible flow." International Journal of Coal Science & Technology 7, no. 3 (2020): 597–610. http://dx.doi.org/10.1007/s40789-020-00314-3.

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Abstract To simulate the transonic atomization jet process in Laval nozzles, to test the law of droplet atomization and distribution, to find a method of supersonic atomization for dust-removing nozzles, and to improve nozzle efficiency, the finite element method has been used in this study based on the COMSOL computational fluid dynamics module. The study results showed that the process cannot be realized alone under the two-dimensional axisymmetric, three-dimensional and three-dimensional symmetric models, but it can be calculated with the transformation dimension method, which uses the para

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29

Khavaran, Abbas, Eugene A. Krejsa, and Chan M. Kim. "Computation of supersonic jet mixing noise for an axisymmetric convergent-divergent nozzle." Journal of Aircraft 31, no. 3 (1994): 603–9. http://dx.doi.org/10.2514/3.46537.

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30

Kim, Chan M., Eugene A. Krejsa, and Abbas Khavaran. "Significance of shock structure on supersonic jet mixing noise of axisymmetric nozzles." AIAA Journal 32, no. 9 (1994): 1920–23. http://dx.doi.org/10.2514/3.12192.

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31

Li, X. D., and J. H. Gao. "Numerical simulation of the generation mechanism of axisymmetric supersonic jet screech tones." Physics of Fluids 17, no. 8 (2005): 085105. http://dx.doi.org/10.1063/1.2033909.

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32

SAKAI, Toshiyuki, Haneda YOSHIAKI, and Shouichiro IIO. "Influence of NPR on Noise Characteristic from an Axisymmetric Supersonic Impinging Jet." Proceedings of Conference of Hokuriku-Shinetsu Branch 2017.54 (2017): C032. http://dx.doi.org/10.1299/jsmehs.2017.54.c032.

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33

Matsuo, Shigeru, Masanori Tanaka, Yumiko Otobe, Hideo Kashimura, Heuy-Dong Kim, and Toshiaki Setoguchi. "Effect of axisymmetric sonic nozzle geometry on characteristics of supersonic air jet." Journal of Thermal Science 13, no. 2 (2004): 121–26. http://dx.doi.org/10.1007/s11630-004-0019-2.

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34

Bolotnova, R. Kh, and V. A. Korobchinskaya. "Simulation the formation process of boiling water flow during depressurization of a high pressure vessel using OpenFoam open source." Proceedings of the Mavlyutov Institute of Mechanics 12, no. 2 (2017): 169–73. http://dx.doi.org/10.21662/uim2017.2.025.

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A numerical study of the initial stage of water outflow process through a thin nozzle from a supercritical state in a two-dimensional axisymmetric setting is performed using the OpenFOAM software open source with the sonicFoam solver. The mathematical model of sonicFoam solver includes the equation of mass conservation, Navier-Stokes equation, internal energy conservation and equation of state of water vapor in the form of a perfect gas. Visualization of calculation results was carried out by the ParaView graphic platform. The features of supersonic high-speed flow regime in a jet accompanied

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35

Rashid, Shagufta, Fahad Nawaz, Adnan Maqsood, et al. "Modeling and Analysis of Shock Reduction through Counterflow Plasma Jets." Mathematical Problems in Engineering 2021 (June 14, 2021): 1–17. http://dx.doi.org/10.1155/2021/5592855.

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The study presents a numerical investigation of aerodynamic drag reduction by implementing a counterflow plasma jet, emanating from the stagnation point of an aerodynamic surface in a supersonic regime with a constant pressure ratio PR = 3 , and compares findings with a conventional opposing jet. The computational study is carried out by solving three-dimensional and axisymmetric Navier–Stokes equations for counterflow plasma-jet interaction. The calculations are performed at free-stream Mach ( M ∞ = 1.4) with sea level stagnation conditions. The weakly ionized argon plasma jet generated by a

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36

Alvi, F. S., P. J. Strykowski, A. Krothapalli, and D. J. Forliti. "Vectoring Thrust in Multiaxes Using Confined Shear Layers." Journal of Fluids Engineering 122, no. 1 (1999): 3–13. http://dx.doi.org/10.1115/1.483220.

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A fluidic scheme is described which exploits a confined countercurrent shear layer to achieve multiaxis thrust vector response of supersonic jets in the absence of moving parts. Proportional and continuous control of jet deflection is demonstrated at Mach numbers up to 2, for pitch vectoring in rectangular nozzles and multiaxis vectoring in axisymmetric nozzles. Secondary mass flow rates less than approximately 2% of the primary flow are used to achieve thrust vector angles exceeding 15 degrees. Jet slew rates up to 180 degrees per second are shown, and the fluidic scheme is examined in both s

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37

Dillmann, Andreas. "Linear potential theory of steady internal supersonic flow with quasi-cylindrical geometry. Part 2. Free jet flow." Journal of Fluid Mechanics 286 (March 10, 1995): 327–57. http://dx.doi.org/10.1017/s0022112095000759.

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By extending the methods of Part 1, the general problem of steady cylindrical supersonic free jet flow is treated in a similar manner to the flow in quasi-cylindrical ducts. It is shown that the presence of a finite pressure jump at the nozzle lip gives rise to a periodic singularity pattern in the flow field. Basic examples of free jet flows are discussed, and for the case of a nearly ideally expanded axisymmetric jet, theoretical Mach—Zehnder interferograms are calculated by analytical integration of the density field. Excellent agreement with experiment proves the validity of linear theory

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38

Yasunobu, Tsuyoshi, Yumiko Otobe, Hideo Kashimura, Shigeru Matsuo, Toshiaki Setoguchi, and Shen Yu. "Characteristic of Hysteresis Phenomena on Shock Wave Structure in Overexpanded Axisymmetric Supersonic Jet." International Journal of Turbo and Jet Engines 26, no. 1 (2009): 1–8. http://dx.doi.org/10.1515/tjj.2009.26.1.1.

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39

Molleson, G. V., and A. L. Stasenko. "Kinetic-thermal effect of a gas-dispersed supersonic jet on an axisymmetric body." High Temperature 52, no. 6 (2014): 881–89. http://dx.doi.org/10.1134/s0018151x14050125.

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40

Bulovich, S. V., A. N. Bazhenov, and R. L. Petrov. "Normal interaction between a supersonic axisymmetric jet and a surface containing a hole coaxial with the jet." Technical Physics 54, no. 12 (2009): 1814–16. http://dx.doi.org/10.1134/s1063784209120160.

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41

Resta, Emanuele, Roberto Marsilio, and Michele Ferlauto. "Thrust Vectoring of a Fixed Axisymmetric Supersonic Nozzle Using the Shock-Vector Control Method." Fluids 6, no. 12 (2021): 441. http://dx.doi.org/10.3390/fluids6120441.

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The application of the Shock Vector Control (SVC) approach to an axysimmetric supersonic nozzle is studied numerically. SVC is a Fluidic Thrust Vectoring (FTV) strategy that is applied to fixed nozzles in order to realize jet-vectoring effects normally obtained by deflecting movable nozzles. In the SVC method, a secondary air flow injection close to the nozzle exit generates an asymmetry in the wall pressure distribution and side-loads on the nozzle, which are also lateral components of the thrust vector. SVC forcing of the axisymmetric nozzle generates fully three-dimensional flows with very

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42

Hornung, H. G. "A model problem for a supersonic gas jet from a moon." Journal of Fluid Mechanics 795 (April 22, 2016): 950–71. http://dx.doi.org/10.1017/jfm.2016.184.

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Some celestial bodies such as planets, moons and comets (here referred to as moons for simplicity) emit jets of material at speeds that in some instances are large enough to escape gravity. Previous investigations have shown this problem to be highly complex, e.g. involving multi-phase flows, phase changes, radiation and gas rarefaction effects. In order to learn from exploring a manageable parameter space, and to provide a limiting case, the present study considers a much simpler model situation in which the material of the jet is an inviscid, non-heat-conducting, perfect gas that issues radi

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43

Chen, Kai, Y. Lawrence Yao, and Vijay Modi. "Gas Jet–Workpiece Interactions in Laser Machining." Journal of Manufacturing Science and Engineering 122, no. 3 (1999): 429–38. http://dx.doi.org/10.1115/1.1285901.

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Laser machining efficiency and quality are closely related to gas pressure, nozzle geometry, and standoff distance. Modeling studies of laser machining rarely incorporate gas effects in part because of the complex structure and turbulent nature of jet flow. In this paper, the interaction of a supersonic, turbulent axisymmetric jet with the workpiece is studied. Numerical simulations are carried out using an explicit, coupled solution algorithm with solution-based mesh adaptation. The model is able to make quantitative predictions of the pressure, mass flow rate as well as shear force at the ma

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44

RAY, PRASUN K., and SANJIVA K. LELE. "Sound generated by instability wave/shock-cell interaction in supersonic jets." Journal of Fluid Mechanics 587 (August 31, 2007): 173–215. http://dx.doi.org/10.1017/s0022112007007306.

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Broadband shock-associated noise is an important component of the overall noise generated by modern airplanes. In this study, sound generated by the weakly nonlinear interaction between linear instability waves and the shock-cell structure in supersonic jets is investigated numerically in order to gain insight into the broadband shock-noise problem. The model formulation decomposes the overall flow into a mean flow, linear instability waves, the shock-cell structure and shock-noise. The mean flow is obtained by solving RANSequations with a k-ε model. Locally parallel stability equations are so

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45

YAMAMOTO, Masami, Norifumi ONO, and Kazuo KOIKE. "607 A Simple Diagnostic Method for Underexpanded Axisymmetric Supersonic Plasma Jet around Shock Waves." Proceedings of Autumn Conference of Tohoku Branch 2013.49 (2013): 175–76. http://dx.doi.org/10.1299/jsmetohoku.2013.49.175.

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46

Yasunobu, Tsuyoshi, Ken Matsuoka, Hideo Kashimura, Shigeru Matsuo, and Toshiaki Setoguchi. "Numerical study for hysteresis phenomena of shock wave reflection in overexpanded axisymmetric supersonic jet." Journal of Thermal Science 15, no. 3 (2006): 220–25. http://dx.doi.org/10.1007/s11630-006-0220-6.

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ALVI, FARRUKH S., HUADONG LOU, CHIANG SHIH, and RAJAN KUMAR. "Experimental study of physical mechanisms in the control of supersonic impinging jets using microjets." Journal of Fluid Mechanics 613 (October 1, 2008): 55–83. http://dx.doi.org/10.1017/s0022112008003091.

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Supersonic impinging jet(s) inherently produce a highly unsteady flow field. The occurrence of such flows leads to many adverse effects for short take-off and vertical landing (STOVL) aircraft such as: a significant increase in the noise level, very high unsteady loads on nearby structures and an appreciable loss in lift during hover. In prior studies, we have demonstrated that arrays of microjets, appropriately placed near the nozzle exit, effectively disrupt the feedback loop inherent in impinging jet flows. In these studies, the effectiveness of the control was found to be strongly dependen

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Chen, Li-Wei, Guo-Lei Wang, and Xi-Yun Lu. "Numerical investigation of a jet from a blunt body opposing a supersonic flow." Journal of Fluid Mechanics 684 (August 30, 2011): 85–110. http://dx.doi.org/10.1017/jfm.2011.276.

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AbstractNumerical investigation of a sonic jet from a blunt body opposing a supersonic flow with a free stream Mach number ${M}_{\infty } = 2. 5$ was carried out using large-eddy simulation for two total pressure ratios of the jet to the free stream, i.e. $\mathscr{P}= 0. 816$ and 1.633. Results have been validated carefully against experimental data. Various fundamental mechanisms dictating the flow phenomena, including shock/jet interaction, shock/shear-layer interaction, turbulent shear-layer evolution and coherent structures, have been studied systematically. Based on the analysis of the f

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Yasunobu, Tsuyoshi, Yumiko Otobe, Hideo Kashimura, and Toshiaki Setoguchi. "808 Numerical Analysis for Hysteresis Phenomenon of Shock Wave in Axisymmetric Over-Expanded Supersonic Jet." Proceedings of Conference of Kyushu Branch 2007 (2007): 281–82. http://dx.doi.org/10.1299/jsmekyushu.2007.281.

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Yasunobu, Tsuyoshi, Yumiko Otobe, Hideo Kashimura, and Toshiaki Setoguchi. "A24 Effect of Pressure Ratio for Hysteresis Phenomenon of Shock Wave in Axisymmetric Supersonic Jet." Proceedings of Conference of Kyushu Branch 2008.61 (2008): 17–18. http://dx.doi.org/10.1299/jsmekyushu.2008.61.17.

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