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Journal articles on the topic 'Jet flow'

Author: Grafiati

Published: 4 June 2021

Last updated: 7 September 2023

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1

Sugimoto, M., T. Shakouchi, K. Hayakawa, M. Okazaki, and M. Izawa. "Particle Laden Impinging Jet Flow from Rectangular Nozzle and Abrasive Jet Machining(Multiphase Flow 2)." Proceedings of the International Conference on Jets, Wakes and Separated Flows (ICJWSF) 2005 (2005): 325–30. http://dx.doi.org/10.1299/jsmeicjwsf.2005.325.

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2

Tabata, Takahide, Satoshi Someya, and Masahiro Nakashima. "JET FLOW ISSUING UPWARD WITH SUBSTANCE DIFFUSION(Jet and Plume)." Proceedings of the International Conference on Jets, Wakes and Separated Flows (ICJWSF) 2005 (2005): 399–404. http://dx.doi.org/10.1299/jsmeicjwsf.2005.399.

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3

Narabayashi, Tadashi, Yukitaka Yamazaki, Hidetoshi Kobayashi, and Toshihiko Shakouchi. "Flow Analysis for Single and Multi-Nozzle Jet Pump(Multiple Jet)." Proceedings of the International Conference on Jets, Wakes and Separated Flows (ICJWSF) 2005 (2005): 267–72. http://dx.doi.org/10.1299/jsmeicjwsf.2005.267.

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4

Imao, Shigeki, Satoshi Kikuchi, Yasuaki Kozato, and Takayasu Hayashi. "FLOW CHARACTERISTICS OF PLANE WALL JET WITH SIDE WALLS ON BOTH SIDES(Wall Jet and Wall Flow)." Proceedings of the International Conference on Jets, Wakes and Separated Flows (ICJWSF) 2005 (2005): 73–78. http://dx.doi.org/10.1299/jsmeicjwsf.2005.73.

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5

Okita, Yuji, Katsutaka Nakamura, Yuuta Shiizaki, and Daisuke Nobuta. "LASER OBSERVATION ON THE INNER FLOW STRUCTURE OF WATER JETS(Water Jet)." Proceedings of the International Conference on Jets, Wakes and Separated Flows (ICJWSF) 2005 (2005): 337–42. http://dx.doi.org/10.1299/jsmeicjwsf.2005.337.

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6

Liffman, K., and A. Siora. "Magnetosonic jet flow." Monthly Notices of the Royal Astronomical Society 290, no. 4 (1997): 629–35. http://dx.doi.org/10.1093/mnras/290.4.629.

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7

Peng, Guoyi. "NUMERICAL STUDY OF CAVITATING VORTEX FLOW IN STARTING SUBMERGED WATER JET(Water Jet)." Proceedings of the International Conference on Jets, Wakes and Separated Flows (ICJWSF) 2005 (2005): 355–60. http://dx.doi.org/10.1299/jsmeicjwsf.2005.355.

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8

Toshihiko, SHAKOUCHI, IRIYAMA Shota, KAWASHIMA Yuki, TSUJIMOTO Koichi, and ANDO Toshitake. "1012 FLOW CHARACTERISTICS OF SUBMERGED FREE JET FLOW FROM PETAL-SHAPED NOZZLE." Proceedings of the International Conference on Jets, Wakes and Separated Flows (ICJWSF) 2013.4 (2013): _1012–1_—_1012–6_. http://dx.doi.org/10.1299/jsmeicjwsf.2013.4._1012-1_.

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9

Mizuki, Kito, Shakouchi Toshihiko, Tsujimoto Koichi, and Ando Toshitake. "1002 RESONANCE JET FLOW FROM NOTCHED ORIFICE NOZZLE." Proceedings of the International Conference on Jets, Wakes and Separated Flows (ICJWSF) 2013.4 (2013): _1002–1_—_1002–6_. http://dx.doi.org/10.1299/jsmeicjwsf.2013.4._1002-1_.

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10

Tatsuya, Ishii, Enomoto Shunji, Nakamura Satoru, and Ishikawa Hitoshi. "1172 JET FLOW CONTROL USING A CLAW MIXER." Proceedings of the International Conference on Jets, Wakes and Separated Flows (ICJWSF) 2013.4 (2013): _1172–1_—_1172–6_. http://dx.doi.org/10.1299/jsmeicjwsf.2013.4._1172-1_.

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11

Lee, H., and Y. B. Chang. "Flow-Induced Vibration of Rod Arrays in a Jet Flow." Journal of Pressure Vessel Technology 112, no. 1 (1990): 46–49. http://dx.doi.org/10.1115/1.2928585.

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Flow-induced vibration of rod arrays in a jet flow was studied experimentally. The rod arrays tested were on square layout with a pitch-to-diameter ratio of 1.32. The rods were found to vibrate with large whirling trajectories when the jet velocity exceeds a critical value. The effects of axial flow velocity and stand-off distance of the rod array from jet exit were also investigated. A design guide for rod arrays subjected to a jet flow is proposed.

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12

Ode, Kosuke, Toshihiro Ohmae, Kenji Yoshida, and Isao Kataoka. "STUDY OF FLOW STRUCTURE IN THE AERATION TANK INDUCED BY TWO PHASE JET FLOW(Multiphase Flow)." Proceedings of the International Conference on Jets, Wakes and Separated Flows (ICJWSF) 2005 (2005): 229–34. http://dx.doi.org/10.1299/jsmeicjwsf.2005.229.

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13

Nakamura, Hirokazu, and Toshihiko Shakouchi. "Flow and Heat Transfer Characteristics of High Temperature Gas-Particle Air Jet Flow(Multiphase Flow 2)." Proceedings of the International Conference on Jets, Wakes and Separated Flows (ICJWSF) 2005 (2005): 319–24. http://dx.doi.org/10.1299/jsmeicjwsf.2005.319.

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14

Lawson, Nicholas J., Mauro P. Arruda, and Malcolm R. Davidson. "CONTROL OF AN OSCILLATORY RECTANGULAR CAVITY JET FLOW BY SECONDARY INJECTION(Cavity Flow and Pulsating Flow)." Proceedings of the International Conference on Jets, Wakes and Separated Flows (ICJWSF) 2005 (2005): 561–65. http://dx.doi.org/10.1299/jsmeicjwsf.2005.561.

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15

Liu, Yuwei, Xinchen Wang, Kangkang Li, and Yaofeng Liu. "Numerical Simulation of Jet Interaction Flow Field with Different Flow Rates." Journal of Physics: Conference Series 2364, no. 1 (2022): 012065. http://dx.doi.org/10.1088/1742-6596/2364/1/012065.

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Abstract In this paper, the complex disturbance flow caused by the interaction of jets with different flow rates and hypersonic incoming flow on a cone-cylinder-skirt of revolution is numerically studied, the typical shock wave structure and the influence range caused by the jet interaction are given, and the effect of the jet flow rate on the interaction flow field is discussed. The results show that the interaction between the jet flow and the incoming flow increases with the rise of the jet flow rate, and the influence range of the wrapping effect enlarges. If the jet flow rate is equivalent to the incoming flow rate, the leading edge separation line forms a closed loop.

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16

Yule, A. J., M. Damou, and D. Kostopoulos. "Modeling confined jet flow." International Journal of Heat and Fluid Flow 14, no. 1 (1993): 10–17. http://dx.doi.org/10.1016/0142-727x(93)90035-l.

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17

Hesp, Patrick A., and Thomas A. G. Smyth. "Jet flow over foredunes." Earth Surface Processes and Landforms 41, no. 12 (2016): 1727–35. http://dx.doi.org/10.1002/esp.3945.

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18

Sundaram, Tharika. "Influence of orifice thickness on the flow field of co-flow jets." Journal of Physics: Conference Series 2484, no. 1 (2023): 012032. http://dx.doi.org/10.1088/1742-6596/2484/1/012032.

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Abstract The present study analyses the numerical simulation results of subsonic flow through co-flow orifices. Analysis is done on the effects of modifying orifice thickness on the co-flow jet characteristics. The combined frontal area of the co-flow jet and central jet is maintained constant (20 mm2). The primary orifice diameter (D) is kept as 3mm and the orifice thickness, i.e the co-flow jet is formed as four segments of a concentric circle around the core jet, and the edge distance between them ranges from 0.16D to 0.5D. The 0.16D co-flow is shown to lengthen the potential core of the main jet at nozzle pressure ratios of 1.2, 1.4, 1.6, and 1.8, but the 0.33D co-flow and the 0.5D co-flow shorten the potential core length, enhancing mixing. The present study analyses the Mach numbers that correspond to the Nozzle Pressure ratios of 1.2, 1.4, 1.6, and 1.8, which are 0.517, 0.71, 0.84, and 0.96, respectively. The 0.5D annular gap is found to be more effective which boosts primary jet mixing.

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19

KOSO, Toru. "ENHANCED MIXING OF A CIRCULAR JET USING AN ANNULAR SYNTHETIC JET ACTUATOR(Flow Control 1)." Proceedings of the International Conference on Jets, Wakes and Separated Flows (ICJWSF) 2005 (2005): 385–90. http://dx.doi.org/10.1299/jsmeicjwsf.2005.385.

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20

Kubik, Anna, and Leonhard Kleiser. "Multiphase Jet Flow in Abrasive Water Jet Cutting." PAMM 9, no. 1 (2009): 457–58. http://dx.doi.org/10.1002/pamm.200910201.

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21

SHAKOUCHI, Toshihiko, Michiyuki UCHIYAMA, Masahiro NISHIO, Koichi TSUJIMOTO, and Toshitake ANDO. "Flow characteristics of micro bubble jet flow." Journal of the Visualization Society of Japan 27, Supplement2 (2007): 61–62. http://dx.doi.org/10.3154/jvs.27.supplement2_61.

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22

Yao, Yufeng, Mohamad Maidi, and Jun Yao. "Effect of Jet Inclination Angle and Hole Exit Shape on Vortical Flow Structures in Low-Reynolds Number Jet in Cross-Flow." Modelling and Simulation in Engineering 2012 (2012): 1–7. http://dx.doi.org/10.1155/2012/632040.

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Numerical studies have been performed to visualize vortical flow structures emerged from jet cross-flow interactions. A single square jet issuing perpendicularly into a cross-flow was simulated first, followed by two additional scenarios, that is, inclined square jet at angles of 30° and 60° and round and elliptic jets at an angle of 90°, respectively. The simulation considers a jet to cross-flow velocity ratio of 2.5 and a Reynolds number of 225, based on the free-stream flow quantities and the jet exit width in case of square jet or minor axis length in case of elliptic jet. For the single square jet, the vortical flow structures simulated are in good qualitative agreement with the findings by other researchers. Further analysis reveals that the jet penetrates deeper into the cross-flow field for the normal jet, and the decrease of the jet inclination angle weakens the cross-flow entrainment in the near-wake region. For both noncircular and circular jet hole shapes, the flow field in the vicinity of the jet exit has been dominated by large-scale dynamic flow structures and it was found that the elliptic jet hole geometry has maximum “lifted-off” effect among three hole configurations studied. This finding is also in good qualitative agreement with existing experimental observations.

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23

Chi, Shaoqing, Yunsong Gu, Yuhang Zhou, and Long Zhou. "Investigation of active flow control of jet deflection rate in passive secondary flow thrust vectoring nozzle." AIP Advances 12, no. 4 (2022): 045324. http://dx.doi.org/10.1063/5.0077291.

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Jet deflection rate is an essential index in the research of thrust vector control technology. The vectoring deflection of the jet is an unsteady flow. In this study, a pulse jet actuator with adjustable frequency was used to control the flow field of the thrust vectoring nozzle. The experimental results show that the unsteady pulse jet with the same characteristic frequency as the separated bubble structure can effectively deflect and adhere to the wall. The deflection rate of the main jet is susceptible to the pulse frequency of the pulse jet, and the flow field can reach the optimal deflection rate only under the unsteady excitation of a specific frequency. The transient flow field results show that the vortex shedding frequency of the flow field can be effectively destroyed by the unsteady excitation of a specific frequency and can evenly distribute the Coanda wall pressure of the vectoring nozzle. This flow phenomenon can increase the pressure difference of the passive secondary flow, accelerate the deflection rate of the main jet, and reduce the deflection hysteresis caused by the separation bubble structure. In this study, the wall deflection rate of the thrust vectoring jet was studied by the active flow control of the unsteady pulsed jet.

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24

Chi, Shaoqing, Yunsong Gu, Yuhang Zhou, and Long Zhou. "Investigation of active flow control of jet deflection rate in passive secondary flow thrust vectoring nozzle." AIP Advances 12, no. 4 (2022): 045324. http://dx.doi.org/10.1063/5.0077291.

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Jet deflection rate is an essential index in the research of thrust vector control technology. The vectoring deflection of the jet is an unsteady flow. In this study, a pulse jet actuator with adjustable frequency was used to control the flow field of the thrust vectoring nozzle. The experimental results show that the unsteady pulse jet with the same characteristic frequency as the separated bubble structure can effectively deflect and adhere to the wall. The deflection rate of the main jet is susceptible to the pulse frequency of the pulse jet, and the flow field can reach the optimal deflection rate only under the unsteady excitation of a specific frequency. The transient flow field results show that the vortex shedding frequency of the flow field can be effectively destroyed by the unsteady excitation of a specific frequency and can evenly distribute the Coanda wall pressure of the vectoring nozzle. This flow phenomenon can increase the pressure difference of the passive secondary flow, accelerate the deflection rate of the main jet, and reduce the deflection hysteresis caused by the separation bubble structure. In this study, the wall deflection rate of the thrust vectoring jet was studied by the active flow control of the unsteady pulsed jet.

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25

Aldabbagh, L. B. Y., I. Sezai, and A. A. Mohamad. "Three-Dimensional Investigation of a Laminar Impinging Square Jet Interaction With Cross-Flow." Journal of Heat Transfer 125, no. 2 (2003): 243–49. http://dx.doi.org/10.1115/1.1561815.

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The flow and heat transfer characteristics of an impinging laminar square jet through cross-flow have been investigated numerically by using the three-dimensional Navier-Stokes and energy equations in steady state. The simulations have been carried out for jet to cross-flow velocity ratios between 0.5 and 10 and for nozzle exit to plate distances between 1D and 6D, where D is the jet width. The complex nature of the flow field featuring a horseshoe vortex has been investigated. The calculated results show that the flow structure is strongly affected by the jet-to-plate distance. In addition, for jet-to-plate spacing of one jet width and for jet to cross-flow velocity ratios less than 2.5 an additional peak occurs at about three-dimensional downstream of the jet impingement point. For high jet to cross-flow ratios two horseshoe vortices form around the jet in the case of small jet-to-plate spacings.

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26

Brodersen, S., D. E. Metzger, and H. J. S. Fernando. "Flows Generated by the Impingement of a Jet on a Rotating Surface: Part I—Basic Flow Patterns." Journal of Fluids Engineering 118, no. 1 (1996): 61–67. http://dx.doi.org/10.1115/1.2817514.

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The results of an experimental study of the flow field resulting from the interaction between an impinging jet and a rotating disk are presented. The resulting flow configuration has applications in turbomachinery, for example, to intensify the local heat transfer at turbine disks. The experiments cover separate measurements of the disk-wall flow, the jet flow and interaction between the two. The flow patterns are investigated over a range of jet Reynolds numbers Rejet = 0.66-104 - 6.80-104 (based on jet diameter) and disk Reynolds numbers Redisk 3.4·105 − 6.2· 105 (based on impingement radius), achieved by varying the jet nozzle diameter, jet flow rate, rotational disk speed and the impingement radius. The measurements included the depth of jet penetration into the wall boundary layer, the travel distance of the jet against the direction of disk rotation, and the turbulent and mean velocity distribution. Another objective of this study concerns the type of flow at the impingement region (jet dominated flow or rotation dominated flow) and the conditions for the transition from one to the other. In the first part of the study, the flow structure of the jet and disk flows as well as the three-dimensional flow fields resulting from the interaction are presented.

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27

Fan, Jing Ming, Chang Ming Fan, and Jun Wang. "Flow Dynamic Simulation of Micro Abrasive Water Jet." Solid State Phenomena 175 (June 2011): 171–76. http://dx.doi.org/10.4028/www.scientific.net/ssp.175.171.

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Simulation of the dynamic characteristics of micro abrasive water jet (MAWJ) is conducted using computation fluid dynamics (CFD) software Fluent 6.3 flow solver. The velocity distributions and particle behaviors of the free jet and impinging jet in and out of the nozzle are investigated under different input and boundary conditions. In the free jet simulation, a reduction in water pressure corresponds to more rapid decay of the jet velocity along the jet axis, whereas particle mass concentration has no influence on the jet velocity. In the impinging jet simulation, the effect of the impingement surface on the flow field increases with a decrease of the stand-off distance. The simulation results in this study provide the foundation for optimizing the nozzle structure and improving cutting efficiency and cutting performance of MAWJ.

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28

Liu, Yanming, Hong Zhang, and Pingchao Liu. "Flow control in supersonic flow field based on micro jets." Advances in Mechanical Engineering 11, no. 1 (2019): 168781401882152. http://dx.doi.org/10.1177/1687814018821526.

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The flow field around supersonic aircraft is usually accompanied by complex flow phenomena, such as shock wave and shock wave/boundary layer interaction, which cause some adverse effects on aircraft performance. Seeking effective flow control methods has been a hot topic for many researchers. As an important method to improve the flow characteristics in supersonic flows, micro jet technology and its control mechanism have been paid much attention. In this article, we used compression corner calculation model and conducted detailed numerical investigations in the supersonic flow field with different injection pressure ratios, various actuation positions, and different nozzle types. The interaction between the micro jets and supersonic upstream flows generates complex flow structures, which contain bow shocks, barrel shocks, Mach disk, counter-rotating vortex pairs, and so on. The flow characteristics with micro jet schemes are superior to those in the no-control case. The controlling performance of micro jet is mainly determined by the following aspects. First, the downwash effect of counter-rotating vortex pairs can bring high-energy fluid into the bottom of the boundary layer to activate low-energy fluid and then strengthen the ability of resisting the flow separations. Second, the bow shock, which is generated upstream of the micro jet, significantly decelerates the downstream flows. Thus, the shock intensity at the corner is weakened and the characteristic of shock wave/boundary layer interaction is improved. In addition, the effective function range of MJ, that is, the distance between the counter-rotating vortex pair and the wall surface, is also an important factor. When both the counter-rotating vortex pairs and the bow shock are further from the wall, the flow characteristics around the corner in a larger area can be improved. Research shows that the micro jet scheme with Laval nozzle gives better controlling effect on shock wave/boundary layer interaction when the injection pressure radio is set to be 0.6, with the actuation location being 20 times the jet outlet diameter upstream of the corner.

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29

ARITA, Masamitsu. "Flow visualization on buoyant jet." JOURNAL OF THE FLOW VISUALIZATION SOCIETY OF JAPAN 8, no. 29 (1988): 91–98. http://dx.doi.org/10.3154/jvs1981.8.91.

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30

TAMANOI, Yu, Yuki WATANABE, Ryota KOBAYASHI, and Kotaro SATO. "Control of Jet Flow direction." Proceedings of Conference of Hokkaido Branch 2020.57 (2020): 29–30. http://dx.doi.org/10.1299/jsmehokkaido.2020.57.29.

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31

Banfi, Andrea, Giuseppe Marchesini, and Graham Smye. "Away-from-jet energy flow." Journal of High Energy Physics 2002, no. 08 (2002): 006. http://dx.doi.org/10.1088/1126-6708/2002/08/006.

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32

Chamani, M. R., and N. Rajaratnam. "Jet Flow on Stepped Spillways." Journal of Hydraulic Engineering 120, no. 2 (1994): 254–59. http://dx.doi.org/10.1061/(asce)0733-9429(1994)120:2(254).

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33

Chanson, Hubert. "Jet Flow on Stepped Spillways." Journal of Hydraulic Engineering 121, no. 5 (1995): 441–48. http://dx.doi.org/10.1061/(asce)0733-9429(1995)121:5(441).

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34

Wang, Xi-kun, and Soon Keat Tan. "Environmental fluid dynamics-jet flow." Journal of Hydrodynamics 22, S1 (2010): 962–67. http://dx.doi.org/10.1016/s1001-6058(10)60067-4.

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35

Dzhaugashtin, K. E. "The critical jet flow regime." Fluid Dynamics 25, no. 3 (1990): 335–39. http://dx.doi.org/10.1007/bf01049812.

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36

Chaudhuri, A. K. "Jet quenching and elliptic flow." Physics Letters B 659, no. 3 (2008): 531–36. http://dx.doi.org/10.1016/j.physletb.2007.11.045.

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37

Armesto, Néstor. "Flow Effects on Jet Profile." Nuclear Physics A 783, no. 1-4 (2007): 133–40. http://dx.doi.org/10.1016/j.nuclphysa.2006.11.009.

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38

Smith, J., and K. Tesima. "Particle flow in a jet." Zeitschrift f�r Physik C Particles and Fields 49, no. 4 (1991): 591–600. http://dx.doi.org/10.1007/bf01483575.

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39

Uruba, Vaclav. "On a Synthetic Jet Flow." PAMM 5, no. 1 (2005): 557–58. http://dx.doi.org/10.1002/pamm.200510255.

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40

INUMARU, Yuki, and Toshiyuki AOKI. "Numerical analysis of purge jet flow and wiping jet flow in continuous galvanizing process." Proceedings of Conference of Kyushu Branch 2019.72 (2019): E11. http://dx.doi.org/10.1299/jsmekyushu.2019.72.e11.

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41

Zhao, Jin, Zhi Ning, and Ming Lü. "Large Eddy Simulation of Two-Phase Flow Pattern and Transformation Characteristics of Flow Mixing Nozzle." Journal of Mechanics 35, no. 5 (2019): 693–704. http://dx.doi.org/10.1017/jmech.2018.51.

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ABSTRACTThe two-phase flow pattern of a flow mixing nozzle plays an important role in jet breakup and atomization. However, the flow pattern of this nozzle and its transformation characteristics are still unclear. A diesel-air injection simulation model of a flow mixing nozzle is established. Then the two-phase flow pattern and transformation characteristics of the flow mixing nozzle is studied using a numerical simulation method. The effect of the air-diesel velocity ratio, ratio of the distance between the tube orifice and nozzle hole and the tube diameter (H/D), and the diesel inlet velocity was studied in terms of the jet breakup diameter (jet diameter at the breakup position) and jet breakup length (length of the diesel jet from the breakup position to the nozzle outlet). The results show that the jet breakup diameter decreases with the decrease in H/D or the increase in the air-diesel velocity ratio and diesel inlet velocity. The jet breakup length increases first and then decreases with the increase in H/D and air-diesel velocity ratio; the trend of the diesel inlet velocity is complicated. In addition, a change in the working conditions also causes some morphological changes that cannot be quantitatively analyzed in the diesel-air flow pattern. The transition characteristics of the flow pattern are analyzed, and it is found that the main reason for the change in the flow pattern is the change in the inertial force of the air, surface tension force, and viscous force of diesel (non-dimensional Reynolds number and Weber number describe the transition characteristics in this paper). The surface tension force of diesel decreases and the viscous force of diesel and inertial force of air increase when the air-diesel velocity ratio increases or H/D decreases. However, the effects of the diesel surface tension force and viscous force effect are much smaller than that of the air inertial force, which changes the diesel-air flow pattern from a drop pattern to a vibration jet pattern, broken jet pattern, and then a chaotic jet pattern.

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42

Kim, Junkyu, Young Min Park, Junseong Lee, et al. "Numerical Investigation of Jet Angle Effect on Airfoil Stall Control." Applied Sciences 9, no. 15 (2019): 2960. http://dx.doi.org/10.3390/app9152960.

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Numerical study on flow separation control is conducted for a stalled airfoil with steady-blowing jet. Stall conditions relevant to a rotorcraft are of interest here. Both static and dynamic stalls are simulated with solving compressible Reynolds-averaged Navier-Stokes equations. It is expected that a jet flow, if it is applied properly, provides additional momentum in the boundary layer which is susceptible to flow separation at high angles of attack. The jet angle can influence on the augmentation of the flow momentum in the boundary layer which helps to delay or suppress the stall. Two distinct jet angles are selected to investigate the impact of the jet angle on the control authority. A tangential jet with a shallow jet angle to the surface is able to provide the additional momentum to the flow, whereas a chord-normal jet with a large jet angle simply averts the external flow. The tangential jet reduces the shape factor of the boundary layer, lowering the susceptibility to the flow separation and delaying both the static and dynamic stalls.

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43

MIYATA, Masafumi. "FLOW STRUCTURE IN DEVELOPING REGION OF ANNULAR JET(Special Nozzle)." Proceedings of the International Conference on Jets, Wakes and Separated Flows (ICJWSF) 2005 (2005): 203–8. http://dx.doi.org/10.1299/jsmeicjwsf.2005.203.

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44

Shogo, Shakouchi, and Uchiyama Tomomi. "1097 MIXING PHENOMENA OF DENSITY STRATIFIED FLUID WITH JET FLOW." Proceedings of the International Conference on Jets, Wakes and Separated Flows (ICJWSF) 2013.4 (2013): _1097–1_—_1097–4_. http://dx.doi.org/10.1299/jsmeicjwsf.2013.4._1097-1_.

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45

Gong, Zhibin, Jie Li, Jixiang Shan, and Heng Zhang. "Numerical Investigation of Powered Jet Effects by RANS/LES Hybrid Methods." Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University 37, no. 3 (2019): 565–71. http://dx.doi.org/10.1051/jnwpu/20193730565.

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For the high-precision simulation of engine jet effects, an improved delayed detached eddy simulation (IDDES) method based on the two-equation shear stress transport (SST) model is developed, and the fifth-order finite-volume weighted essentially non-oscillatory (WENO) scheme is employed to enhance accuracy of spatial discretization, and then numerical investigation of powered jet effects by RANS/LES hybrid methods is carried out. The effects of the grid distributions and the accuracy of the spatial schemes are discussed during the RANS/LES validation analysis on the fully expanded jet flow and Acoustic Reference Nozzle (ARN) jet flow. The results show that, by enlarging the grid density and improving the accuracy of the spatial schemes, the velocity distributions in the jet flow can be better predicted, the non-physical steady flow after the jet nozzle can be shortened, the instantaneous flow structures are clearer and the turbulent intensities are more accurate. Then IDDES simulation of turbofan engine jet flow is carried out. The mixing characteristics of the external fan jet flow and internal core jet flow as well as the ambient flow are obtained, and the three-dimensional turbulent structures are also given.

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46

NAKASHIMA, Masahiro, Shingo MATSUDA, Takahide TABATA, and Akira RINOSHIKA. "Control of Jet Flow by Reciprocal Oscillating Flow." Journal of the Visualization Society of Japan 27, Supplement2 (2007): 65–66. http://dx.doi.org/10.3154/jvs.27.supplement2_65.

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47

Anwar, Habib O. "Flow of Surface Buoyant Jet in Cross Flow." Journal of Hydraulic Engineering 113, no. 7 (1987): 892–904. http://dx.doi.org/10.1061/(asce)0733-9429(1987)113:7(892).

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48

Wong, Kok Cheong. "Numerical Investigation of a Crossflow Jet in a Rectangular Microchannel." Applied Mechanics and Materials 284-287 (January 2013): 849–53. http://dx.doi.org/10.4028/www.scientific.net/amm.284-287.849.

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Abstract:

The present numerical study is conducted in three dimensional to investigate the crossflow of an external round jet and a horizontal stream of microchannel flow. The results of heat transfer performance for the cases with and without transverse jet are compared. The patterns of different crossflow jet were analyzed to understand the flow and heat transfer characteristics. The effect of jet nozzle position on the heat transfer is investigated. Generally, the heat transfer performance increases with the jet Reynolds number. However, some cases of weak jet are found to cause lower heat transfer rate relative to the case without external jet. When vertical weak jet encounter strong horizontal flow, the horizontal flow is dominant that the jet cannot reach the microchannel bottom wall but imposes resistance to the horizontal flow. The investigation on the jet nozzle location shows that the jet nozzle location closer to the channel inlet gives better heat transfer performance.

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49

Wan, Zhao, Yangaoxiao Fu, Xinguang Wang, and Qi Chen. "Numerical Simulation of Orbit Controlled Hot-gas Lateral Jet of the triangular plate with rudder." Journal of Physics: Conference Series 2280, no. 1 (2022): 012024. http://dx.doi.org/10.1088/1742-6596/2280/1/012024.

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Abstract Hypersonic interception weapons have high requirements for the efficiency and accuracy of the control system. As an effective control approach, the thermochemical non-equilibrium effect of jet flow must be considered in order to accurately predict the aerodynamic characteristic. At present, relevant researches are mostly focused on the low-flow rate hot jet, while numerical simulation and wind tunnel test studies on high-flow rate hot jet are rare. In this paper, the interaction flow field of the rail-controlled jet at the altitude of 60Km and 70Km has been simulated by solving the three-dimensional viscous fluid governing equations. The influence of the thermalchemical non-equilibrium effect of the jet interaction on the flow field characteristics and aerodynamic characteristics of the aircraft was analyzed. The primary results show that: (1) The flow fields of the cold-gas jet, frozen-gas jet and hot-gas jet have significant differences under the high-flow rate jet condition, which is mainly reflected the size and the pressure value of the separation region before the nozzle. The separation region length of the cold-gas jet is approximately twice that of the hot-gas jet and the length of the frozen-gas jet is between them; (2)Jet interaction will increase the surface pressure of the aircraft and reduce the skin-friction. When Ma=25, the aerodynamic interaction of hot jet is only about 30% of that of cold jet; (3) Jet interaction on aerodynamic characteristics increases with altitudes. With the increase of Mach number, the difference between the predicted results of hot jet and cold jet is enlarged because of the enhancement of the thermochemical non-equilibrium effect.

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50

Wan, Zhao, Yangaoxiao Fu, Xinguang Wang, and Qi Chen. "Numerical Simulation of Orbit Controlled Hot-gas Lateral Jet of the triangular plate with rudder." Journal of Physics: Conference Series 2280, no. 1 (2022): 012024. http://dx.doi.org/10.1088/1742-6596/2280/1/012024.

Full text

Abstract:

Abstract Hypersonic interception weapons have high requirements for the efficiency and accuracy of the control system. As an effective control approach, the thermochemical non-equilibrium effect of jet flow must be considered in order to accurately predict the aerodynamic characteristic. At present, relevant researches are mostly focused on the low-flow rate hot jet, while numerical simulation and wind tunnel test studies on high-flow rate hot jet are rare. In this paper, the interaction flow field of the rail-controlled jet at the altitude of 60Km and 70Km has been simulated by solving the three-dimensional viscous fluid governing equations. The influence of the thermalchemical non-equilibrium effect of the jet interaction on the flow field characteristics and aerodynamic characteristics of the aircraft was analyzed. The primary results show that: (1) The flow fields of the cold-gas jet, frozen-gas jet and hot-gas jet have significant differences under the high-flow rate jet condition, which is mainly reflected the size and the pressure value of the separation region before the nozzle. The separation region length of the cold-gas jet is approximately twice that of the hot-gas jet and the length of the frozen-gas jet is between them; (2)Jet interaction will increase the surface pressure of the aircraft and reduce the skin-friction. When Ma=25, the aerodynamic interaction of hot jet is only about 30% of that of cold jet; (3) Jet interaction on aerodynamic characteristics increases with altitudes. With the increase of Mach number, the difference between the predicted results of hot jet and cold jet is enlarged because of the enhancement of the thermochemical non-equilibrium effect.

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