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Journal articles on the topic 'Smoke Flow Visualization'

Author: Grafiati

Published: 4 June 2021

Last updated: 7 September 2023

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1

Raval, D., S. V. Jain, A. M. Acharii, and K. Ghosh. "Design and analysis of smoke flow visualization apparatus for wind tunnel." IOP Conference Series: Materials Science and Engineering 1206, no. 1 (November 1, 2021): 012014. http://dx.doi.org/10.1088/1757-899x/1206/1/012014.

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Abstract In the present study, the design and analysis of smoke generator are done for the low-speed wind tunnel. The wind tunnel fan is fitted with the Variable Frequency Drive to produce the wind speed in the range of 3 to 32 m/s with fan speed of 150 to 1500 rpm. The design of smoke generator was done according to Preston Sweeting mist generator principle corresponding to the free stream velocity of 3 m/s. A controlled smoke generator consisting of kerosene reservoir, controlled heater, blower, liquid column height adjustment mechanism, valves etc. was designed and fabricated. The smoke generator produced the smoke at the rate of 154 cm3/s which was close to the design flow rate of 149 cm3/s. To supply the required quantity of smoke in the wind tunnel, the smoke rake of NACA 0010 profile was developed and installed in the rapid contraction section of the wind tunnel to achieve the streamlined flow. The parametric studies were done on the smoke generator at different power inputs and its effects were studied on smoke temperature, smoke discharge and boiling time of the kerosene. The flow visualization was carried out on NACA 0015 airfoil model and the images were captured to examine the flow physics around them under different operating conditions.

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2

Miller, L. S., and E. Irani. "Simple method of supersonic flow visualization using smoke." AIAA Journal 30, no. 1 (January 1992): 278–79. http://dx.doi.org/10.2514/3.10913.

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3

Balachander, Aakash, Akash Alase, K. Adithya Menon, G. Mahendra Perumal, and B. T. Kannan. "Smoke based visualization of turbulent swirl jet flow." IOP Conference Series: Materials Science and Engineering 912 (September 12, 2020): 022011. http://dx.doi.org/10.1088/1757-899x/912/2/022011.

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4

Yuan, Zhi, Ye Zhao, Fan Chen, Sean Reber, Cheng-Chang Lu, and Yang Chen. "Detail-preserving compression for smoke-based flow visualization." Journal of Visualization 22, no. 1 (November 19, 2018): 51–64. http://dx.doi.org/10.1007/s12650-018-0526-y.

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5

Goodfellow, S. D., S. Yarusevych, and P. E. Sullivan. "Smoke-wire flow visualization of a synthetic jet." Journal of Visualization 16, no. 1 (December 18, 2012): 9–12. http://dx.doi.org/10.1007/s12650-012-0155-9.

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6

Forney, G. P., D. Madrzykowski, K. B. McGrattan, and L. Sheppard. "Understanding fire and smoke flow through modeling and visualization." IEEE Computer Graphics and Applications 23, no. 4 (July 2003): 6–13. http://dx.doi.org/10.1109/mcg.2003.1210858.

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7

Koca, Kemal, Mustafa Serdar Genç, and Halil Hakan Açıkel. "Experimental investigation on effect of partial flexibility at low aspect ratio airfoil - Part II: Installation both on suction and pressure surface." EPJ Web of Conferences 269 (2022): 01028. http://dx.doi.org/10.1051/epjconf/202226901028.

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In this experimental study, flow over NACA 4412 airfoil with flexible membrane mounted both on suction surface and pressure surface was investigated at Reynolds number of 5x104 and different angles of attack. The smoke-wire visualization method was used for flow visualization to demonstrate flow phenomena as laminar separation bubble (LSB), leading edge separation and tip vortices. A constant temperature anemometer (CTA) was used for measuring flow over the partially flexible airfoil. Concerning the flow visualization, smoke-wire experiment was been conducted at z/c=0.1 and z/c=0.4. Besides, hot-wire experiment by means of CTA was employed to measure flow properties including values of velocity, turbulence statistics and Reynold stress over both uncontrolled and controlled airfoil. The results showed that partially flexible airfoil had several benefits compared with the uncontrolled airfoil. The results for this partially flexible airfoil were mainly lower size of LSB, higher stall angle of attack, ensuring more stable flow characteristics and more aerodynamic performance.

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8

Ristic, Slavica. "A - a view in the invisible." Theoretical and Applied Mechanics 40, no. 1 (2013): 87–119. http://dx.doi.org/10.2298/tam1301087r.

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Flow visualization is an important topic in, experimental and computational fluid dynamics and has been the subject of research for many years. This paper presents an overview of flow visualization techniques. The physical basis and applications of different visualization methods for subsonic, transonic and supersonic flow in wind and water tunnels are described: direct injection methods, (smoke, dye, fog and different small particles), gas and hydrogen bubbles, , flow visualization by tufts, oil, liquid crystals, pressure and temperature sensitive paints, shadow, schlieren, interferometry, Laser Doppler Anemometry, Particle Image Velocimetry and other special techniques. Almost all presented photos have been recorded during tests in laboratories of MTI Belgrade.

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9

Lee, Sang-Joon, and Sang-Hyun Lee. "SYNCHRONIZED SMOKE-WIRE TECHNIQUE FOR FLOW VISUALIZATION OF TURBULENT FLOWS." Journal of Flow Visualization and Image Processing 6, no. 1 (1999): 65–78. http://dx.doi.org/10.1615/jflowvisimageproc.v6.i1.60.

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10

SETA, SHIGEYUKI, ZIN SUGAWARA, MITURU YABUSHITA, YOSHIO HARA, TOSHIHIRO OKA, and MACHIKA URABE. "EXPERIMENTS OF FLOW VISUALIZATION IN CLEAN ROOM BY CIGARETTE SMOKE." JOURNAL OF THE FLOW VISUALIZATION SOCIETY OF JAPAN 7, Supplement (1987): 93–96. http://dx.doi.org/10.3154/jvs1981.7.supplement_93.

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11

YAMAMOTO, Masao, Yoshihiro MATSUOKA, Yasuhiko NAKAMURA, Keiichi WATANABE, Yuri AOYAMA, and Noboru KOIKE. "Flow Visualization in a Curved Diffuser Using Smoke Wire Method." Journal of the Visualization Society of Japan 15, Supplement1 (1995): 85–88. http://dx.doi.org/10.3154/jvs.15.supplement1_85.

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12

YAMAMOTO, Masao, Yoshihiro MATSUOKA, Keiichi WATANABE, Yuri AOYAMA, and Noboru KOIKE. "Flow Visualization in a Curved Diffuser Using Smoke Wire Method." Journal of the Visualization Society of Japan 16, no. 1Supplement (1996): 63–66. http://dx.doi.org/10.3154/jvs.16.1supplement_63.

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13

Yonaga, Ryuji, Masahide Hatano, and Toshihiko Okamoto. "Smoke Tunnel Flow Visualization Study on Miniature Trailing-Edge Flaps." Journal of the Visualization Society of Japan 18, Supplement1 (1998): 157–60. http://dx.doi.org/10.3154/jvs.18.supplement1_157.

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14

Fukamachi, N., Y. Ohya, and Y. Nakamura. "An improvement of the smoke-wire method of flow visualization." Fluid Dynamics Research 7, no. 1 (January 1991): 23–29. http://dx.doi.org/10.1016/0169-5983(91)90003-2.

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15

Porch, W. M., S. Barr, W. E. Clements, J. A. Archuleta, A. B. Fernandez, C. W. King, W. D. Neff, and R. P. Hosker. "Smoke Flow Visualization in a Tributary of a Deep Valley." Bulletin of the American Meteorological Society 70, no. 1 (January 1989): 30–35. http://dx.doi.org/10.1175/1520-0477(1989)070<0030:sfviat>2.0.co;2.

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16

YOSHIDA, Seiichi, and Hiromu HASHIMOTO. "1030 Flow visualization around Dragonfly's wing with smoke-wire method." Proceedings of the JSME annual meeting 2006.5 (2006): 353–54. http://dx.doi.org/10.1299/jsmemecjo.2006.5.0_353.

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17

Pellessier, John E., Heather E. Dillon, and Wyatt Stoltzfus. "Schlieren Flow Visualization and Analysis of Synthetic Jets." Fluids 6, no. 11 (November 15, 2021): 413. http://dx.doi.org/10.3390/fluids6110413.

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This work explores several low-cost methods for the visualization and analysis of pulsed synthetic jets for cooling applications. The visualization methods tested include smoke, Schlieren imaging, and thermography. The images were analyzed using Proper Orthogonal Decomposition (POD) and numerical methods for videos. The results indicated that for the specific nozzle studied, the optimal cooling occurred at a frequency of 80 Hz, which also corresponded to the highest energy in the POD analysis. The combination of Schlieren photography and POD is a unique contribution as a method for the optimization of synthetic jets.

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18

von Funck, W., T. Weinkauf, H. Theisel, and H. P. Seidel. "Smoke Surfaces: An Interactive Flow Visualization Technique Inspired by Real-World Flow Experiments." IEEE Transactions on Visualization and Computer Graphics 14, no. 6 (November 2008): 1396–403. http://dx.doi.org/10.1109/tvcg.2008.163.

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19

Cheng, K. C., and Liqiu Wang. "Secondary Flow Phenomena in Rotating Radial Straight Pipes." International Journal of Rotating Machinery 2, no. 2 (1995): 103–11. http://dx.doi.org/10.1155/s1023621x9500025x.

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Flow visualization results for secondary flow phenomena near the exit of a rotating radial-axis straight pipe (length ࡁ = 82 cm, inside diameter d = 3.81 cm, ࡁ/d 21.52) are presented to study the stabilizing (relaminarization) and destabilizing (early transition from laminar to turbulent flow) effects of Coriolis forces for Reynolds numbers Re = 500 ∼ 4,500 and rotating speeds n = 0 ∼ 200 rpm. The flow visualization was realised by smoke injection method. The main features of the transition phenomena are disclosed for Re = 1,500 and 4,500. The observed secondary flow patterns are found to be quite different from those obtained by theoretical or numerical analysis with one pair of symmetric and steady counter-rotating vortices. The practical implications of the visualization study are pointed out.

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20

AKASHI, Koichiro. "Partial Flow Visualization around an Airfoil by the Smoke Wind Tunnel." Journal of the Visualization Society of Japan 15, Supplement2 (1995): 101–4. http://dx.doi.org/10.3154/jvs.15.supplement2_101.

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21

Yarusevych, Serhiy, Pierre E. Sullivan, and John G. Kawall. "Smoke-Wire Flow Visualization in Separated Flows at Relatively High Velocities." AIAA Journal 47, no. 6 (June 2009): 1592–95. http://dx.doi.org/10.2514/1.43539.

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22

KIKUCHI, Takao. "An Apparatus for Flow Visualization by Smoke in Circular Wind Tunnel." Journal of the Japan Society for Aeronautical and Space Sciences 47, no. 548 (1999): 360–63. http://dx.doi.org/10.2322/jjsass.47.360.

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23

HATANO, Masahide, Toshio OKAMOTO, and Osamu IKARI. "Flow visualization around a complex airfoil by the smoke-tube method." Journal of the Visualization Society of Japan 12, no. 1Supplement (1992): 243–46. http://dx.doi.org/10.3154/jvs.12.1supplement_243.

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24

Kulkarni, P. R., S. N. Singh, and V. Seshadri. "Flow Visualization Studies of Exhaust Smoke-Superstructure Interaction on Naval Ships." Naval Engineers Journal 117, no. 1 (January 2005): 41–56. http://dx.doi.org/10.1111/j.1559-3584.2005.tb00320.x.

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25

Genç, Mustafa Serdar, Halil Hakan Açıkel, and Kemal Koca. "Experimental investigation on effect of partial flexibility at low aspect ratio airfoil – Part I: Installation on suction surface." EPJ Web of Conferences 269 (2022): 01017. http://dx.doi.org/10.1051/epjconf/202226901017.

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Effects of flexible membrane mounted over suction surface of NACA 4412 airfoil were experimentally investigated at Reynolds number of 5x104 and low aspect ratio (AR=1) in this paper. The smoke-wire visualization method has been performed for flow visualization to demonstrate flow phenomena as laminar separation bubble (LSB), leading edge separation at z/c=0.4 and tip vortices at z/c=0.1. Values of velocity, Reynolds stress and turbulence statistics were measured by means of a constant temperature anemometer (CTA) system. Results of smoke-wire experiment revealed that size and height of LSB formed along z/c=0.4 at lower angles of attack such as α=8° was mitigated. Moreover, stall phenomenon as a result of boundary layer separation was apparently postponed at higher angles of attack. Velocity value was increased, whereas values of Reynold stress and turbulent kinetic energy was decreased with reduction of amount of fluctuations in flow. Consequently, using flexible membrane over suction surface of airfoil allowed the LSB to be mitigated or extinguished, resulting in exhibition of more stable flow characteristics.

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26

Dobrucali, Erinc. "Flow visualization and analytical study on the exhaust gas diffusion of a frigate." Pomorstvo 35, no. 2 (December 22, 2021): 308–17. http://dx.doi.org/10.31217/p.35.2.13.

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Wind tunnel flow visualization tests were conducted to analyse the efflux velocity impacts and the yaw angle on the smoke dispersion of the exhaust for a generic frigate. An analytical study was also implemented to obtain the exhaust plume trajectories. The 1/100 scale generic frigate, having a platform for helicopters on the aft of the ship, was built and employed during the experimental study. The forward and astern cruises of the frigate were considered. It is found that the plume height and the exhaust gases momentum increase with the velocity ratio. The problem of smoke nuisance was observed for the ratios with low velocity such as K=0.2. The plume was also directed towards the helicopter platform when the yaw angles are higher than 10°. The experimental results are compared with the analytical solutions for three different velocity ratios. The compliance between the experimental and analytical results is found to be consistent.

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27

Johnson, L. R., and J. R. Shanebrook. "Flow visualization with air and smoke in a bypass graft model under steady flow conditions." Journal of Biomechanics 28, no. 10 (October 1995): 1237–41. http://dx.doi.org/10.1016/0021-9290(94)00183-5.

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28

Caletka, Petr, Ondrej Pech, Jan Jedelsky, Frantisek Lizal, and Miroslav Jicha. "Comparison of methods for flow border detection in images of smoke visualization." EPJ Web of Conferences 114 (2016): 02009. http://dx.doi.org/10.1051/epjconf/201611402009.

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29

Gao, N., and X. H. Liu. "An improved smoke-wire flow visualization technique using capacitor as power source." Theoretical and Applied Mechanics Letters 8, no. 6 (December 2018): 378–83. http://dx.doi.org/10.1016/j.taml.2018.06.010.

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30

Finlay, W. H., Y. Guo, and D. Olsen. "Inferring secondary flows from smoke or dye flow visualization: Two case studies." Physics of Fluids A: Fluid Dynamics 5, no. 11 (November 1993): 2689–701. http://dx.doi.org/10.1063/1.858732.

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31

Kenjeres, S., S. B. Gunarjo, and K. Hanjalic. "Visualization of air flow and smoke spreading for realistic indoor-climate situations." Journal of Visualization 7, no. 4 (December 2004): 268. http://dx.doi.org/10.1007/bf03181526.

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32

Liang, X., and B. R. Ramaprian. "Visualization of the Wing-Tip Vortex in Temporal and Spatial Pressure Gradients." Journal of Fluids Engineering 113, no. 3 (September 1, 1991): 511–15. http://dx.doi.org/10.1115/1.2909527.

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The evolution of the longitudinal vortex in the near field of a rectangular wing has been visualized using smoke and laser light sheet. The smoke photographs have been used to obtain qualitative and some quantitative information on the effect of small temporal and spatial pressure gradients on the evolution of the vortex in this region. The experiments indicate that even small temporal retardation of the flow can produce a significant increase in the vortex size. This effect becomes larger with increase in retardation, angle of incidence and distance downstream from the trailing edge. Also, vortex “breakdown” was found to occur in many temporal-deceleration experiments. The vortex evolution was, however, found to be relatively insensitive to the presence of small spatial adverse pressure gradients along the flow direction. The study is preliminary in nature and needs to be supported by more extensive quantitative measurements.

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33

Cheng, K. C., and F. P. Yuen. "Flow Visualization Experiments on Secondary Flow Patterns in an Isothermally Heated Curved Pipe." Journal of Heat Transfer 109, no. 1 (February 1, 1987): 55–61. http://dx.doi.org/10.1115/1.3248067.

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Secondary flow patterns at the exit of a 180 deg bend (tube inside diameter d = 1.99 cm, radius of curvature Rc = 10.85 cm) are presented to illustrate the combined effects of centrifugal and buoyancy forces in hydrodynamically and thermally developing entrance region of an isothermally heated curved pipe with both parabolic and turbulent entrance velocity profiles. Three cases of upward, horizontal, and downward-curved pipe flows are studied for constant wall temperatures Tw=55–91°C, Dean number range K=22–1209 and ReRa=1.00×106–8.86×107. The flow visualization was realized by the smoke injection method. The secondary flow patterns shown are useful for future comparison with numerical predictions and confirming theoretical models. The results can be used to assess qualitatively the limit of the applicability of the existing correlation equations for laminar forced convection in isothermally heated curved pipes without buoyancy effects.

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34

Chernoray, Valeriy, and Yuriy Litvinenko. "Investigation of a Plane Wall Jet by Piv." Siberian Journal of Physics 4, no. 2 (July 1, 2009): 19–26. http://dx.doi.org/10.54362/1818-7919-2009-4-2-19-26.

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The structure of a plane wall jet by means of smoke visualization and PIV measurements is investigated experimentally. Instantaneous and ensemble-averaged the flow fields for different cross-sections are presented. Features of the development and interaction of the Kelvin-Helmholz vortex and longitudinal structures are shown.

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35

Yocum, A. M., and W. F. O’Brien. "Separated Flow in a Low-Speed Two-Dimensional Cascade: Part I—Flow Visualization and Time-Mean Velocity Measurements." Journal of Turbomachinery 115, no. 3 (July 1, 1993): 409–20. http://dx.doi.org/10.1115/1.2929268.

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This study was conducted for the purpose of providing a more fundamental understanding of separated flow in cascades and to provide performance data for fully stalled blade rows. Cascades of a single blade geometry and a solidity of unity were studied for three stagger angles and the full range of angle of attack, extending well into the stalled flow regime. Results are presented from flow visualization and time-mean velocity measurements of stalled flow in the cascade. Surface and smoke flow visualization revealed that the blade stagger angle is a key parameter in determining the location of the separation line and the occurrence of propagating stall. Time-mean velocity measurements obtained with a dual hot split-film probe also showed that the separated velocity profiles within the blade passages and the profiles in the wake have distinctly different characteristics depending on the stagger angle.

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36

Yin, Changchun, and Greg Hodges. "3D animated visualization of EM diffusion for a frequency-domain helicopter EM system." GEOPHYSICS 72, no. 1 (January 2007): F1—F7. http://dx.doi.org/10.1190/1.2374706.

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The electromagnetic fields inside the earth are calculated by continuation downward of the electromagnetic (EM) solutions at the location of a frequency-domain helicopter electromagnetic (HEM) sensor. Models examined using the continuation approach include a layered isotropic and anisotropic earth. The finite-element approach is used to model 2D structures of a dipping contact or a dipping dike. By incorporating a time factor, we display the EM diffusion in the earth (change in direction and amplitude of the EM field through time) as 3D animated vectors or contours. The propagation of the EM smoke ring, influenced by the resistivity and structure of the earth, is apparent from the dynamic presentations. The current propagates downward and outward with time, becoming wider and more diffuse, and the phase varies with time, depth, and outward distance. The downward propagation of EM fields is slower in more conductive geology. In a layered isotropic earth, the current ring is symmetric with no vertical current flow for both vertical and horizontal dipole transmitters. In anisotropic or 2D structures; however, the current flow is significantly distorted resulting in vertical current flow and nonsymmetric smoke rings.

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37

Wang, H. P., S. J. Olson, R. J. Goldstein, and E. R. G. Eckert. "Flow Visualization in a Linear Turbine Cascade of High Performance Turbine Blades." Journal of Turbomachinery 119, no. 1 (January 1, 1997): 1–8. http://dx.doi.org/10.1115/1.2841006.

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Multiple smoke wires are used to investigate the secondary flow near the endwall of a plane cascade with blade shapes used in high-performance turbine stages. The wires are positioned parallel to the endwall and ahead of the cascade, within and outside the endwall boundary layer. The traces of the smoke generated by the wires are visualized with a laser light sheet illuminating various cross sections around the cascade. During the experiment, a periodically fluctuating horseshoe vortex system of varying number of vortices is observed near the leading edge of the cascade. A series of photographs and video tapes was taken in the cascade to trace these vortices. The development and evolution of the horseshoe vortex and the passage vortex are clearly resolved in the photographs. The interation between the suction side leg of the horseshoe vortex and the passage vortex is also observed in the experiment. A vortex induced by the passage vortex, starting about one-fourth of the curvilinear distance along the blade on the suction surface, is also found. This vortex stays close to the suction surface and above the passage vortex in the laminar flow region on the blade. From this flow visualization, a model describing the secondary flows in a cascade is proposed and compared with previous published models. Some naphthalene mass transfer results from a blade near an endwall are cited and compared with the current model. The flows inferred from the two techniques are in good agreement.

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38

Miao, Jr-Ming, and Hou-Chei Chang. "FLOW VISUALIZATION OF SMOKE SCREEN FORMATION FOR A RECTANGULAR VEHICLE IN DYNAMIC MOTION." Journal of Flow Visualization and Image Processing 15, no. 3 (2008): 235–60. http://dx.doi.org/10.1615/jflowvisimageproc.v15.i3.40.

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39

Zeutzius, Michael, Shigeru Matsuo, Toshihiro Nakano, Toshiaki Setoguchi, and Kenji Kaneko. "127 Visualization of Flow Field around a Space Plane Using Smoke Wire Method." Journal of the Visualization Society of Japan 15, Supplement2 (1995): 109–12. http://dx.doi.org/10.3154/jvs.15.supplement2_109.

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40

ISOBE, Yoshinari, Yasuo KATOH, Atsushi NOMURA, Masanobu KAGAWA, and Eiji UCHIYAMA. "Flow visualization around the rotating straight grinding wheel using the smoke wire method." Journal of the Visualization Society of Japan 16, Supplement2 (1996): 65–68. http://dx.doi.org/10.3154/jvs.16.supplement2_65.

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41

SHINDO, Shojiro, Takeshi AKASAKA, and Masakazu ISHIZAKI. "Three Dimensional Flow Visualization Around a Wing Tip at 40m/s Using Smoke." Journal of the Visualization Society of Japan 21, no. 81 (2001): 81–84. http://dx.doi.org/10.3154/jvs.21.81.

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42

Park, Nak Gyu, Sung Hoon Baik, Seung Kyu Park, and Dong Lyul Kim. "Visualization of a smoke flow field by using a lidar and DIC technique." Journal of the Korean Physical Society 67, no. 10 (November 2015): 1726–31. http://dx.doi.org/10.3938/jkps.67.1726.

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43

Xu, Guo Jun, Jing Zhang, Zhao Yang Yang, and Ti Yin Li. "The Research of Temperature Measuring System Based on Digital-Temperature Sensor." Applied Mechanics and Materials 595 (July 2014): 232–36. http://dx.doi.org/10.4028/www.scientific.net/amm.595.232.

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The principle and the realization method of the temperature measuring system which based on the temperature data acquisition chip-DS18B20 and the serial communication chip MAX1480B were introduced. Hardware principle diagram, software flow chart and main subprogram are also given. The dependability of the system was strengthened by using visualization technology and ionic smoke sensing technology.

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44

Choi, Kwing-So. "Near-wall structure of a turbulent boundary layer with riblets." Journal of Fluid Mechanics 208 (November 1989): 417–58. http://dx.doi.org/10.1017/s0022112089002892.

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A detailed wind tunnel study has been carried out on the near-wall turbulence structure over smooth and riblet wall surfaces under zero pressure gradient. Time-average quantities as ‘well as conditionally sampled profiles were obtained using hotwire/film anemometry, along with a simultaneous flow visualization using the smoke-wire technique and a sheet of laser light. The experimental results indicated a significant change of the structure in the turbulent boundary layer near the riblet surface. The change was confined within a small volume of the flow close to the wall surface. A conceptual model for the sequence of the bursts was then proposed based on an extensive study of the flow visualization, and was supported by the results of conditionally sampled velocity fields. A possible mechanism of turbulent drag reduction by riblets is discussed.

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45

Hsiao, Fei-Bin, and Jiann-Min Huang. "On the Dynamics of Flow Structure Development in an Excited Plane Jet." Journal of Fluids Engineering 116, no. 4 (December 1, 1994): 714–20. http://dx.doi.org/10.1115/1.2911840.

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Coherent structure dynamics in the developing region of a plane jet under acoustic excitation is studied experimentally by means of hot-wire measurements and smoke-wire flow visualization. The mean and fluctuation velocity properties, such as mean and fluctuation intensities in both streamwise and transverse directions, turbulent shear stress variations, and the turbulent energy production and energy convection phenomena, are carefully investigated. The results indicate that flow property behavior is closely related to vortex formation and the merging processes, which are the dominant mechanisms governing flow behavior in the developing region of a plane jet.

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46

Banerjee, R., K. M. Isaac, L. Oliver, and W. Breig. "Features of Automotive Gas Tank Filler Pipe Two-Phase Flow: Experiments and Computational Fluid Dynamics Simulations." Journal of Engineering for Gas Turbines and Power 124, no. 2 (March 26, 2002): 412–20. http://dx.doi.org/10.1115/1.1445439.

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Extensive flow visualization in an automotive fuel filler pipe made visible by introducing dyes and smoke in water and air, respectively, were conducted for nominal flow rates of 4–18 liters per minute. Video and still cameras were used for imaging. Features of the flow such as laminar-to-turbulent transition, progressive development of strong swirl along filler pipe axis, air entrainment, and mixing with the liquid were observed in the experiments. The experimental observations were supported by computational fluid dynamics (CFD) simulations of the flow which also showed features such as swirl and air entrainment.

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47

Al-Kayiem, Hussain H. "Visualization of Flow Field and Wake over Clean and Under-Loaded Wings." Applied Mechanics and Materials 629 (October 2014): 24–29. http://dx.doi.org/10.4028/www.scientific.net/amm.629.24.

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Experimental details of the flow field and wake over airfoils and 2-D wings are time and cost consumption. In this study, the flow visualization technique was adopted to investigate the flow field surrounding NACA4412 airfoil. The investigations were carried out in smoke tunnel, operating at low Reynolds number in a range of 105. The airfoil was tested in two operational cases: first as clean wing and the second as under-loaded wing by attached missile model. The experiments were conducted at various angles of attack as 00, 50,100, 150and 200. It was found that the under-load of external body under the wing is influencing the flow structure over the wing. Also, the wake after the external body is swirling, leading to very complicated wake interaction. The results from the work can support the numerical simulation and the prediction of the laminar to turbulent transition and the separation and wake interaction of high lift airfoil flow fields.

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48

Ishii, J., and S. Honami. "A Three-Dimensional Turbulent Detached Flow With a Horseshoe Vortex." Journal of Engineering for Gas Turbines and Power 108, no. 1 (January 1, 1986): 125–30. http://dx.doi.org/10.1115/1.3239858.

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Static and dynamic mechanisms in a three-dimensional, turbulent, detached flow with a horseshoe vortex, which is encountered in turbomachinery, are clarified experimentally. Flow directional intermittency is obtained by a thermal tuft probe and wall pressure fluctuation survey is performed. Flow visualization is also made by the oil film and smoke wire technique. Four types of vortices exist in the detached region. These vortices are generated by the different process. The detached region is divided into two parts: the region I and II. The flow in the region II, including the detachment point, has dynamic characteristics with low-frequency fluctuation. A new flow model in the detached region is proposed.

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49

Miller, Fletcher J., and Howard D. Ross. "Smoke visualization of the gas-phase flow during flame spread across a liquid pool." Symposium (International) on Combustion 27, no. 2 (January 1998): 2715–22. http://dx.doi.org/10.1016/s0082-0784(98)80127-6.

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50

Pierce, F. J., and I. K. Tree. "The Mean Flow Structure on the Symmetry Plane of a Turbulent Junction Vortex." Journal of Fluids Engineering 112, no. 1 (March 1, 1990): 16–22. http://dx.doi.org/10.1115/1.2909361.

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The mean flow structure on the symmetry plane of a turbulent junction vortex is documented. A two-channel, two-color LDV system allowed nonintrusive measurements of the two velocity components on the symmetry plane. Extensive measurements were made in and around the separation point and within the junction vortex system, both very close to the floor and to the leading edge of the body generating the vortex system. Real-time smoke visualizations confirmed a region of strongly time-variant flow with large changes in the scale and position of the principal vortex structure. The extensive velocity field data are correlated with high quality surface visualizations and surface pressure measurements. The mean velocity measurements show one large well-defined vortex structure and one singular saddle point of separation on the symmetry plane. The transverse vorticity field computed from the extensive velocity field suggests a very strong but small second, counter rotating vortex located in the extreme corner formed by the floor and leading edge of the body. The surface flow visualization suggests only one clear separation line. The single pair of counter rotating vortices revealed by these detailed LDV velocity measurements is in agreement with two independent studies which used multiple orifice pressure probes. This measured two vortex model is not in agreement with the frequently pictured four vortex flow model, inferred from surface flow visualizations, showing two pairs of counter rotating vortices.

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