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Journal articles on the topic 'Stereo particle image velocimetry (SPIV)'

Author: Grafiati

Published: 4 June 2021

Last updated: 1 February 2022

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1

Chen, Qiu Hua, Xu Lai, and Jin Zou. "SPIV Analysis of the Tip Vortex Evolution of a Horizontal Axis Wind Turbine." Advanced Materials Research 860-863 (December 2013): 256–61. http://dx.doi.org/10.4028/www.scientific.net/amr.860-863.256.

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The present paper evaluates the tip vortex evolution of a horizontal axis wind turbine model using the stereo particle image velocimetry technology. The measurements of the wake region up to 2.7 diameters downstream are first conducted using the phase locked technique based on two high speed CCD cameras. Parameters that describe the helical vortex wake, such as the velocity, helicoidal pitch and vortex vorticity, are presented at two tip speed ratios. The vortex interaction and stability of helical vortex filaments within wind turbine wake are seen throughout the measurement domain. The results show the wake structure varies with tip speed ratio, and the helicoidal pitch of tip vortex trajectory reduces while the diffusion of tip vortex is faster with increasing tip speed ratio.

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Shukla, Dhwanil, and Narayanan Komerath. "Multirotor Drone Aerodynamic Interaction Investigation." Drones 2, no. 4 (December 3, 2018): 43. http://dx.doi.org/10.3390/drones2040043.

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Aerodynamic interactions between rotors are important factors affecting the performance of in-plane multirotor Unmanned Air Vehicles (UAVs) or drones, which are the majority of small size UAVs (or mini-drones). Optimal design requires knowledge of the flow features. The low Reynolds number of many UAV rotors raises the question of how these features differ from those expected by traditional analytical methods for rotorcraft. Aerodynamics of a set of side-by-side rotors in hover over a range of rotor separation and Reynolds number is studied using high-speed Stereo Particle Image Velocimetry (SPIV) and performance measurements. The instantaneous and time-averaged SPIV data presented here indicate an increase in inter-rotor wake interactions with decrease in rotor spacing and Reynolds number. A dip in rotor efficiency at small rotor spacing at low Reynolds number is observed through thrust and torque measurements. The basic components of in-plane multirotor wake and velocity profiles are identified and discussed to help generalize the findings to a wide range of drones. However, the data provide confidence in traditional analysis tools, with small modifications.

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3

El Lababidy, S., N. Bose, P. Liu, D. Walker, and F. Di Felice. "Experimental Analysis of the Near Wake from a Ducted Thruster at True and Near Bollard Pull Conditions Using Stereo Particle Image Velocimetry (SPIV)." Journal of Offshore Mechanics and Arctic Engineering 127, no. 3 (March 3, 2005): 191–96. http://dx.doi.org/10.1115/1.1951770.

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Thrusters working at low advance coefficients are employed in a wide range of offshore and marine applications on Floating, Production, Storage, and Offloading (FPSO) systems; shuttle tankers; tug boats; and mobile offshore units. Therefore, an understanding of the flow around the thrusters is of great practical interest. Despite this interest, there is lack of knowledge in the description of the hydrodynamic characteristics of a ducted thruster’s wake at bollard pull and low advance coefficient values. This work was aimed at providing detailed data about the hydrodynamic characteristics of a Dynamic Positioning (DP) thruster near wake flow at different low advance coefficient values. Wake measurements were made during cavitation tunnel tests carried out on a ducted propeller model at the Italian Ship Model Basin (INSEAN), Rome, Italy. Through these experiments, the DP thruster near wake velocity components at different downstream axial planes, up to 1.5 diameters downstream, were obtained using a Stereoscopic Particle Image Velocimetry (SPIV) system. These experiments were carried out at different advance coefficient (J) values [bollard pull (J=0), J=0.4 and J=0.45].

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4

Szmyd, Janusz, Marian Branny, Michal Karch, Waldemar Wodziak, Marek Jaszczur, and Remigiusz Nowak. "Experimental and Numerical Analysis of the air Flow in T-Shape Channel Flow / Eksperymentalna i numeryczna analiza przepływu powietrza przez skrzyżowanie kanałów w kształcie litery T." Archives of Mining Sciences 58, no. 2 (June 1, 2013): 333–48. http://dx.doi.org/10.2478/amsc-2013-0023.

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This paper presents the results of experimental and numerical investigations of air flow through the crossing of a mining longwall and ventilation gallery. The object investigated consists of airways (headings) arranged in a T-shape. Maintained for technological purposes, the cave is exposed particularly to dangerous accumulations of methane. The laboratory model is a certain simplification of a real longwall and ventilation gallery crossing. Simplifications refer to both the object’s geometry and the air flow conditions. The aim of the research is to evaluate the accuracy with which numerical simulations model the real flow. Stereo Particle Image Velocimetry (SPIV) was used to measure all velocity vector components. Three turbulence models were tested: standard k-ε, k-ε realizable and the Reynolds Stress Model (RSM). The experimental results have been compared against the results of numerical simulations. Good agreement is achieved between all three turbulence model predictions and measurements in the inflow and outflow of the channel. Large differences between the measured and calculated velocity field occur in the cavity zone. Two models, the standard k-ε and k-ε realizable over-predict the measure value of the streamwise components of velocity. This causes the ventilation intensity to be overestimated in this domain. The RSM model underestimates the measure value of streamwise components of velocity and therefore artificially decreases the intensity of ventilation in this zone. The RSM model provides better predictions than the standard k-ε and k-ε realizable in the cavity zone.

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5

Cantrak, Djordje, Novica Jankovic, and Dejan Ilic. "Investigation of the turbulent swirl flow in pipe generated by axial fans using PIV and LDA methods." Theoretical and Applied Mechanics 42, no. 3 (2015): 211–22. http://dx.doi.org/10.2298/tam1503211c.

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In this paper is presented experimental investigation of the turbulent swirl flow in pipe generated by axial fans. Two various models of industrial axial fans are used. One of these is axial fan W30, model AP 400, Minel, Serbia and has seven blades and outer diameter 0.397m. Second axial fan SP30 is model TGT/2-400-6, S&P, Spain, has six blades and outer diameter 0.386m. This results with greater clearance in the second case. Blades were adjusted for both fans at the angle of 30? at the outer diameter. Test rig length is 27.74-D, where D is average inner diameter app. 0.4 m. Measurements are performed in two measuring sections downstream the axial fans (z/D = 3.35 and z/D = 26.31) with one-component laser Doppler anemometry (LDA) system and stereo particle image velocimetry (SPIV). Obtained Reynolds numbers, calculated on the basis of the average axial velocity (Um) in the first measuring section are for fan SP30 Re = 226757, while for fan W30 Re = 254010. Integral flow parameters are determined such as average circulation and swirl number. Significant downstream axial velocity transformation occurs for both fans, while circumferential velocity is decreased, but non-dimensional velocity profile remains the same. Circumferential velocity distribution for both fans in the central zone corresponds to the solid body, while in r/R > 0.4, where D = 2R, distribution is more uniform. Radial velocity in the case of fan SP30 has almost zero values in the measuring section z/D = 3.35, while its values are significantly increased in the downstream section with the maximum in the vortex core region. On the contrary radial velocity decreases downstream for fan W30 and has also maximum value in the vortex core region for both measuring sections. Level of turbulence, skewness and flatness factors are calculated on the basis of the experimental data. The highest levels of turbulence for circumferential velocity are reached in the vortex core region for both fans. It is shown how statistical moments of the third and fourth order differ from the values for normal Gaussian distribution. In this paper are also analyzed velocity fields by use of SPIV.

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6

Bhattacharya, Sayantan, John J. Charonko, and Pavlos P. Vlachos. "Stereo-particle image velocimetry uncertainty quantification." Measurement Science and Technology 28, no. 1 (November 24, 2016): 015301. http://dx.doi.org/10.1088/1361-6501/28/1/015301.

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7

Kähler, C. J., and J. Kompenhans. "Fundamentals of multiple plane stereo particle image velocimetry." Experiments in Fluids 29, no. 7 (December 31, 2000): S070—S077. http://dx.doi.org/10.1007/s003480070009.

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8

El Lababidy, S., N. Bose, P. Liu, and F. Di Felice. "Detailed Analysis of the Wake of a DP Thruster Emphasizing Comparison Between LDV and SPIV Techniques." Journal of Offshore Mechanics and Arctic Engineering 128, no. 2 (November 4, 2005): 81–88. http://dx.doi.org/10.1115/1.2185680.

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To provide experimental data on the hydrodynamic characteristics and features of dynamic positioning (DP) thrusters under variable operating conditions, wake measurements were performed on a DP thruster model using 2D laser Doppler velocimetry (LDV) and stereoscopic particle image velocimetry (SPIV). These tests were performed with and without a nozzle and over a range of advance coefficient values including the bollard pull condition. In this paper, a detailed analysis of the hydrodynamic characteristics of the wake at a plane equal to a distance of 0.5 diameters downstream from the thruster, at advance coefficient values of 0, 0.4, and 0.45 are presented for both the LDV and SPIV measurements showing a comparison between the results of each technique. The effect of the duct and of changes in the advance coefficient values is presented in this paper.

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9

Gil-Prieto, Daniel, David G. MacManus, Pavlos K. Zachos, Geoffrey Tanguy, and Kevin R. Menzies. "Convoluted Intake Distortion Measurements Using Stereo Particle Image Velocimetry." AIAA Journal 55, no. 6 (June 2017): 1878–92. http://dx.doi.org/10.2514/1.j055467.

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10

Deng, Rui, Shigang Wang, Wanzhen Luo, and Tiecheng Wu. "Experimental Study on the Influence of Bulbous Bow Form on the Velocity Field around the Bow of a Trimaran Using Towed Underwater 2D-3C SPIV." Journal of Marine Science and Engineering 9, no. 8 (August 21, 2021): 905. http://dx.doi.org/10.3390/jmse9080905.

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In this study, particle image velocimetry was applied to measure the flow field around the bow region of a trimaran with different appendages. The dimensionless axial velocity u/U in test planes 1 and 2 of the testing model was measured by using a towed underwater stereoscopic particle image velocimetry (SPIV) system. Based on the measured flow field data, the local sinkage values in test planes 1 and 2 of the testing model with different appendages at speeds of 1.766 and 2.943 m/s were presented. In addition, the effects of speed, bulbous bow type, T foils, and bow wave on the axial velocity u/U were studied in detail. The acquired experimental data help in understanding the distribution of the flow field around the ship bow, and the data can also act as a reference to verify computational fluid dynamics (CFD) results.

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11

Manolesos, Marinos, and Spyros G. Voutsinas. "Study of a stall cell using stereo particle image velocimetry." Physics of Fluids 26, no. 4 (April 2014): 045101. http://dx.doi.org/10.1063/1.4869726.

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12

Fei, R., and W. Merzkirch. "Investigations of the measurement accuracy of stereo particle image velocimetry." Experiments in Fluids 37, no. 4 (July 20, 2004): 559–65. http://dx.doi.org/10.1007/s00348-004-0843-x.

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13

Zhang, Zherui, and Ronald J. Hugo. "Stereo particle image velocimetry applied to a vortex pipe flow." Experiments in Fluids 40, no. 3 (November 18, 2005): 333–46. http://dx.doi.org/10.1007/s00348-005-0071-z.

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14

Yazdi, Sina G., Larissa Huetter, Paul D. Docherty, Petra N. Williamson, Don Clucas, Mark Jermy, and Patrick H. Geoghegan. "A Novel Fabrication Method for Compliant Silicone Phantoms of Arterial Geometry for Use in Particle Image Velocimetry of Haemodynamics." Applied Sciences 9, no. 18 (September 11, 2019): 3811. http://dx.doi.org/10.3390/app9183811.

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Cardiovascular diseases (CVDs) are one of the leading causes of death globally. In-vitro measurement of blood flow in compliant arterial phantoms can provide better insight into haemodynamic states and therapeutic procedures. However, current fabrication techniques are not capable of producing thin-walled compliant phantoms of complex shapes. This study presents a new approach for the fabrication of compliant phantoms suitable for optical measurement. Two 1.5× scaled models of the ascending aorta, including the brachiocephalic artery (BCA), were fabricated from silicone elastomer Sylgard-184. The initial phantom used the existing state of the art lost core manufacturing technique with simple end supports, an acrylonitrile butadiene styrene (ABS) additive manufactured male mould and Ebalta-milled female mould. The second phantom was produced with the same method but used more rigid end supports and ABS male and female moulds. The wall thickness consistency and quality of resulting stereoscopic particle image velocimetry (SPIV) were used to verify the fidelity of the phantom for optical measurement and investigation of physiological flow fields. However, the initial phantom had a rough surface that obscured SPIV analysis and had a variable wall thickness (range = 0.815 mm). The second phantom provided clear particle images and had a less variable wall thickness (range = 0.317 mm). The manufacturing method developed is suitable for fast and cost-effective fabrication of different compliant arterial phantom geometries.

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15

Kitajima, H. D., K. S. Sundareswaran, T. Z. Teisseyre, K. Pekkan, D. de Zelicourt, M. A. Fogel, and A. P. Yoganathan. "3-D Stereo-particle image velocimetry in the total cavopulmonary connection." Journal of Biomechanics 39 (January 2006): S304. http://dx.doi.org/10.1016/s0021-9290(06)84184-9.

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16

HUTCHINS, N., W. T. HAMBLETON, and IVAN MARUSIC. "Inclined cross-stream stereo particle image velocimetry measurements in turbulent boundary layers." Journal of Fluid Mechanics 541, no. -1 (October 11, 2005): 21. http://dx.doi.org/10.1017/s0022112005005872.

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17

Schröder, A., and J. Kompenhans. "Investigation of a turbulent spot using multi-plane stereo particle image velocimetry." Experiments in Fluids 36, no. 1 (August 23, 2003): 82–90. http://dx.doi.org/10.1007/s00348-003-0644-7.

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18

Tanguy, Geoffrey, David G. MacManus, Pavlos Zachos, Daniel Gil-Prieto, and Eric Garnier. "Passive Flow Control Study in an S-Duct Using Stereo Particle Image Velocimetry." AIAA Journal 55, no. 6 (June 2017): 1862–77. http://dx.doi.org/10.2514/1.j055354.

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19

Lapsa, Andrew P., and Werner J. A. Dahm. "Stereo particle image velocimetry of nonequilibrium turbulence relaxation in a supersonic boundary layer." Experiments in Fluids 50, no. 1 (June 4, 2010): 89–108. http://dx.doi.org/10.1007/s00348-010-0897-x.

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20

Cerutti, Juan José, Costantino Sardu, Gioacchino Cafiero, and Gaetano Iuso. "Active Flow Control on a Square-Back Road Vehicle." Fluids 5, no. 2 (April 21, 2020): 55. http://dx.doi.org/10.3390/fluids5020055.

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An experimental investigation focused on the manipulation of the wake generated by a square back car model is presented. Four continuously-blowing rectangular slot jets were mounted on the rear face of a 1:10 commercial van model. Load cell measurements evidence drag reduction for different forcing configurations, reaching a maximum of 12% for lateral and bottom jets blowing. The spectral analysis of the pressure fluctuations evidence, for all forced cases, an energy attenuation with respect to the natural case, especially close to the shedding frequency. An energy budget highlighted the most efficient forcing configurations accounting for both the drag reduction and the power required to feed the blowing system. Two main configurations are considered: the maximum drag reduction and the best compromise, yielding 5% drag reduction and a convenient energy balance. Particle Image Velocimetry (pPIV) and stereoscopic PIV (sPIV) experiments were performed allowing the three-dimensional reconstruction of the wake in the three considered configurations. Consistently with static and fluctuating pressure measurements, sPIV results reveal a dramatic change in the wake structure when the jets blow in the maximum drag reduction configuration. Conversely, the best compromise configuration reveals a wake structure similar to the natural one.

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21

Grant, Ian, X. Pan, F. Romano, and X. Wang. "Neural-Network Method Applied to the Stereo Image Correspondence Problem in Three-Component Particle Image Velocimetry." Applied Optics 37, no. 17 (June 10, 1998): 3656. http://dx.doi.org/10.1364/ao.37.003656.

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22

Marassi, M., P. Castellini, M. Pinotti, and L. Scalise. "Cardiac valve prosthesis flow performances measured by 2D and 3D-stereo particle image velocimetry." Experiments in Fluids 36, no. 1 (January 1, 2004): 176–86. http://dx.doi.org/10.1007/s00348-003-0693-y.

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23

Vanderwel, Christina, and Stavros Tavoularis. "Measurements of turbulent diffusion in uniformly sheared flow." Journal of Fluid Mechanics 754 (August 7, 2014): 488–514. http://dx.doi.org/10.1017/jfm.2014.406.

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AbstractThe diffusion of a plume of dye in uniformly sheared turbulent flow in a water tunnel was investigated using simultaneous stereoscopic particle image velocimetry (SPIV) and planar laser-induced fluorescence (PLIF). Maps of the mean concentration and the turbulent concentration fluxes in planes normal to the plume axis were constructed, from which all components of the second-order turbulent diffusivity tensor were determined for the first time. Good agreement between the corresponding apparent and true diffusivities was observed. The turbulent diffusivity tensor was found to have strong off-diagonal components, whereas the streamwise component appeared to be counter-gradient. The different terms in the advection–diffusion equation were estimated from the measurements and their relative significance was discussed. All observed phenomena were explained by physical arguments and the results were compared to previous ones.

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24

Li, Jun, Jun Hu, and Chenkai Zhang. "Experimental investigation of the tip leakage flow in a low-speed multistage axial compressor." Science Progress 103, no. 3 (July 2020): 003685042095107. http://dx.doi.org/10.1177/0036850420951070.

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Casing pressure measurements and Stereoscopic Particle-Image Velocimetry (SPIV) measurements are used together to characterize the behavior of the rotor tip leakage flow at both the design and near-stall conditions in a low-speed multistage axial compressor. A three-dimensional Navier-Stokes solver is also performed for the multistage compressor and the prediction of tip leakage flow is compared with SPIV data and casing dynamic static pressure data. During the experiment 10 high-frequency Kulite transducers are mounted in the outer casing of the rotor 3 to investigate the complex flow near the compressor casing and Fourier analyses of the dynamic static pressure on the casing of the rotor 3 are carried out to investigate the tip leakage flow characteristics. At the same time, the two CCD cameras are arranged at the same side of the laser light sheet, which is suitable for investigating unsteady tip leakage flow in the multistage axial compressor. The SPIV measurements identify that the tip leakage flow exists in the rotor passage. The influence of tip leakage flow leads to the existence of low axial velocity region in the rotor passage and the alternating regions of positive and negative radial velocity indicates the emergence of tip leakage vortex (TLV). The trajectory of the tip leakage vortex moves from the suction surface toward the pressure surface of adjacent blade, which is aligned close to the rotor at the design point (DP). However, the tip leakage vortex becomes unstable and breaks down at the near-stall point (NS), making the vortex trajectory move upstream in the rotor passage and causing a large blockage in the middle of the passage.

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25

Campanardi, Gabriele, Donato Grassi, Alex Zanotti, Emmanouil M. Nanos, Filippo Campagnolo, Alessandro Croce, and Carlo L. Bottasso. "Stereo particle image velocimetry set up for measurements in the wake of scaled wind turbines." Journal of Physics: Conference Series 882 (August 2017): 012003. http://dx.doi.org/10.1088/1742-6596/882/1/012003.

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26

HATAOKA, Satoru, Haruhiko GEJIMA, and Koji FUKAGATA. "S0530301 Measurement of vortex shedding suppression effects by plasma actuators using stereo particle image velocimetry." Proceedings of Mechanical Engineering Congress, Japan 2015 (2015): _S0530301——_S0530301—. http://dx.doi.org/10.1299/jsmemecj.2015._s0530301-.

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27

Yuan, Bing-xiang, Wen-wu Chen, Tong Jiang, Yi-xian Wang, and Ke-ping Chen. "Stereo particle image velocimetry measurement of 3D soil deformation around laterally loaded pile in sand." Journal of Central South University 20, no. 3 (March 2013): 791–98. http://dx.doi.org/10.1007/s11771-013-1550-7.

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28

Haigermoser, C., F. Scarano, and M. Onorato. "Investigation of the flow in a circular cavity using stereo and tomographic particle image velocimetry." Experiments in Fluids 46, no. 3 (October 25, 2008): 517–26. http://dx.doi.org/10.1007/s00348-008-0577-2.

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29

Guo, Chun-yu, Tie-cheng Wu, Wan-zhen Luo, Xin Chang, Jie Gong, and Wen-xuan She. "Experimental study on the wake fields of a Panamax Bulker based on stereo particle image velocimetry." Ocean Engineering 165 (October 2018): 91–106. http://dx.doi.org/10.1016/j.oceaneng.2018.07.037.

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30

Hiratsuka, Masaki, Shinichiro Ito, Keita Miyasaka, and Akihisa Konno. "Stereo three-dimensional particle image velocimetry measurement and aerodynamic force analysis of non-spinning soccer balls." Proceedings of the Institution of Mechanical Engineers, Part P: Journal of Sports Engineering and Technology 234, no. 2 (February 12, 2020): 146–53. http://dx.doi.org/10.1177/1754337119898355.

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A knuckle shot, resulting from non-spinning kicking, is an essential technique in soccer. The irregular flight path of the knuckle shot is caused by the aerodynamic force from the three-dimensional twin vortices generated in the wake behind the ball. However, the detailed behavior of the twin vortices and relation between the jet flow and the acting forces on the balls is still not understood. In addition, a more thorough understanding of the effect of ball panels on the formation of twin vortices and jet flow is important to develop balls with high controllability. To study the effect of the ball panel shape on the flight path, stereo three-dimensional particle image velocimetry wake flow measurements and synchronized force measurements were performed on various soccer balls. It was confirmed that the aerodynamic force on the ball is produced by the jet flow generated by the vortices in the wake flow. The directions of the force followed the changes of the jet flow, and the magnitude of the force was strongly associated with the flow rate of the jet. Moreover, the shape of the ball panels, especially the groove volume, determines the critical Reynolds number and the fluttering of the balls.

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Chopski, Steven G., Owen M. Rangus, Carson S. Fox, William B. Moskowitz, and Amy L. Throckmorton. "Stereo-Particle Image Velocimetry Measurements of a Patient-Specific Fontan Physiology Utilizing Novel Pressure Augmentation Stents." Artificial Organs 39, no. 3 (January 16, 2015): 228–36. http://dx.doi.org/10.1111/aor.12364.

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FILATYEV, S., M. THARIYAN, R. LUCHT, and J. GORE. "Simultaneous stereo particle image velocimetry and double-pulsed planar laser-induced fluorescence of turbulent premixed flames." Combustion and Flame 150, no. 3 (August 2007): 201–9. http://dx.doi.org/10.1016/j.combustflame.2007.02.005.

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Shi, Lei, Hongwei Ma, and Lixiang Wang. "Analysis of Different POD Processing Methods for SPIV-Measurements in Compressor Cascade Tip Leakage Flow." Energies 12, no. 6 (March 15, 2019): 1021. http://dx.doi.org/10.3390/en12061021.

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Though the proper orthogonal decomposition (POD) method has been widely adopted in flow analysis, few publications have systematically studied the influence of different POD processing methods on the POD results. This paper investigates the effects of different decomposition regions and decomposition dimensionalities on POD decomposition and reconstruction concerning the tip flow in the compressor cascade. Stereoscopic particle image velocimetry (SPIV) measurements in the blade channel are addressed to obtain the original flow field. Through vortex core identification, development of the tip leakage vortex along the chord is described. Afterwards, each plane is energetically decomposed by POD. Using the identified vortex core center as the geometric center, the effects of different decomposition regions with respect to the vortex core are analyzed. Furthermore, the effects of different single velocity-components as well as their combination are compared. The effect of different decomposition regions on the mode 1 energy fraction mainly impacts the streamwise velocity component. Though the addition of W velocity component in the decomposition does change the spatial structures of high-order modes, it does not change the dynamic results of reconstruction using a finite number of POD modes. UV global analysis is better for capturing the kinetic physics of the tip leakage vortex (TLV) wandering.

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Velte, Clara M., and Martin O. L. Hansen. "Investigation of flow behind vortex generators by stereo particle image velocimetry on a thick airfoil near stall." Wind Energy 16, no. 5 (July 25, 2012): 775–85. http://dx.doi.org/10.1002/we.1541.

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35

Wen, Xin, Jiajun Liu, Donguk Kim, Yingzheng Liu, and Kyung Chun Kim. "Study on three-dimensional flow structures of a sweeping jet using time-resolved stereo particle image velocimetry." Experimental Thermal and Fluid Science 110 (January 2020): 109945. http://dx.doi.org/10.1016/j.expthermflusci.2019.109945.

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Geneste, Damien, Hugues Faller, Florian Nguyen, Vishwanath Shukla, Jean-Philippe Laval, Francois Daviaud, Ewe-Wei Saw, and Bérengère Dubrulle. "About Universality and Thermodynamics of Turbulence." Entropy 21, no. 3 (March 26, 2019): 326. http://dx.doi.org/10.3390/e21030326.

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This paper investigates the universality of the Eulerian velocity structure functions using velocity fields obtained from the stereoscopic particle image velocimetry (SPIV) technique in experiments and direct numerical simulations (DNS) of the Navier-Stokes equations. It shows that the numerical and experimental velocity structure functions up to order 9 follow a log-universality (Castaing et al. Phys. D Nonlinear Phenom. 1993); this leads to a collapse on a universal curve, when units including a logarithmic dependence on the Reynolds number are used. This paper then investigates the meaning and consequences of such log-universality, and shows that it is connected with the properties of a “multifractal free energy”, based on an analogy between multifractal and thermodynamics. It shows that in such a framework, the existence of a fluctuating dissipation scale is associated with a phase transition describing the relaminarisation of rough velocity fields with different Hölder exponents. Such a phase transition has been already observed using the Lagrangian velocity structure functions, but was so far believed to be out of reach for the Eulerian data.

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Van Buren, Tyler, Edward Whalen, and Michael Amitay. "Vortex formation of a finite-span synthetic jet: effect of rectangular orifice geometry." Journal of Fluid Mechanics 745 (March 18, 2014): 180–207. http://dx.doi.org/10.1017/jfm.2014.77.

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AbstractThe formation and evolution of flow structures of a finite-span synthetic jet issuing into a quiescent flow were investigated experimentally using stereoscopic particle image velocimetry (SPIV). The effect of two geometrical parameters, the orifice aspect ratio and the neck length, were explored at a Strouhal number of 0.115 and a Reynolds number of 615. Normalized orifice neck lengths of 2, 4 and 6 and aspect ratios of 6, 12, and 18 were examined. It was found that the effect of the aspect ratio is much larger than the effect of the neck length, and as the aspect ratio increases the size of the edge vortices decreases and the presence of secondary structures is more evident. Moreover, axis switching was observed and its streamwise location increases as the aspect ratio increases. The effect of the neck length on the flow structures and the evolution of the synthetic jet was found to be secondary, where the effect was only in the very near field (i.e. close to the jet’s orifice).

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Liu, Baojie, Hongwei Wang, Huoxing Liu, Hongjun Yu, Haokang Jiang, and Maozhang Chen. "Experimental Investigation of Unsteady Flow Field in the Tip Region of an Axial Compressor Rotor Passage at Near Stall Condition With Stereoscopic Particle Image Velocimetry." Journal of Turbomachinery 126, no. 3 (July 1, 2004): 360–74. http://dx.doi.org/10.1115/1.1748367.

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Stereoscopic particle image velocimetry (SPIV) was applied to a large-scale low-speed compressor facility with the configuration of the two CCD cameras placed on each side of the light sheet to make the measurement of the vortices in the cross flow section possible and to avoid the disturbance from the light sheet containing periscope-type probe. Instantaneous velocity and vorticity distributions were successfully documented at the tip region of the rotor at near stall condition. The measurement results clearly revealed the generation and evolution of the tip leakage vortex. Comparing to design condition, the tip leakage vortex at near stall condition generates and breaks down earlier and interacts more violently with mainstream, which causes large blockage and much loss. Whether corner vortex exists or not is the primary difference between near stall and design condition. Differing from the leakage vortex, the corner vortex is composed of multiple vortices developed from the suction surface of the rotor blade. The key mechanism for the generation of the corner vortex is that the rotation of the rotor has different effect on the evolution of positive vortices and negative vortices, which makes the positive vortices dissipates faster than the negative ones, the vortices at the rotor exit therefore bear mainly negative vortices, which induces the fluids to rotate clockwise at the corner and forms the corner vortex.

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Mejia-Alvarez, R., and K. T. Christensen. "Wall-parallel stereo particle-image velocimetry measurements in the roughness sublayer of turbulent flow overlying highly irregular roughness." Physics of Fluids 25, no. 11 (November 2013): 115109. http://dx.doi.org/10.1063/1.4832377.

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Brücker, C. "Study of the three-dimensional flow in a T-junction using a dual-scanning method for three-dimensional scanning-particle-image velocimetry (3-D SPIV)." Experimental Thermal and Fluid Science 14, no. 1 (January 1997): 35–44. http://dx.doi.org/10.1016/s0894-1777(96)00110-0.

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Sudhakar, S., A. Chandankumar, and L. Venkatakrishnan. "Influence of propeller slipstream on vortex flow field over a typical micro air vehicle." Aeronautical Journal 121, no. 1235 (November 17, 2016): 95–113. http://dx.doi.org/10.1017/aer.2016.114.

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ABSTRACTAn experimental study has been carried out to explore the effect of propeller-induced slipstream on the vortex flow field on a fixed-wing Micro Air Vehicle (MAV). Experiments were conducted at a freestream velocity of 10 m/s, corresponding to a Reynolds number based on a root chord of about 1.6 × 105. Surface flow topology on the surface of the MAV wing at propeller-off and propeller-on conditions was captured using surface oil flow visualisation at four angles of incidence. The mean off-body flow over the MAV was documented in the four spanwise planes at different chord position using Stereoscopic Particle Image Velocimetry (SPIV) technique at angle-of-attack of 24° for both conditions. The oil flow visualisation showed minimal differences in flow patterns for propeller-off and propeller-on conditions at 10° and 15° incidence. The small asymmetry between port and starboard side observed at 20° during the propeller-off condition became significantly pronounced at 24°. The fuselage stub which is necessary for housing the motor of the propeller was seen to have a significant effect on the flow symmetry at large incidences that can occur when the MAV encounters sudden vertical gusts. Switching on the propeller restored the symmetry at both incidences. SPIV measurements were carried out at the incidence of 24° which exhibited the highest asymmetry. The off-body data shows the re-establishment of symmetry during propeller-on condition owing to the increase in the magnitude of spanwise and vertical velocities as a result of the propeller slipstream. The findings emphasise the importance of considering the propeller flow and design of the motor housing while evaluating the aerodynamics of low-aspect-ratio MAVs.

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Wu, Tiecheng, Wanzhen Luo, Dapeng Jiang, Rui Deng, and Yulong Li. "Stereo Particle Image Velocimetry Measurements of the Wake Fields Behind A Panamax Bulker Ship Model Under the Ballast Condition." Journal of Marine Science and Engineering 8, no. 6 (May 30, 2020): 397. http://dx.doi.org/10.3390/jmse8060397.

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Particle image velocimetry is applied in this study to measure the wake flow field of a Panamax Bulker ship model under the ballast condition. This investigation revealed that the Froude number is 0.167. The time-averaged velocity, turbulent fluctuations, turbulent kinetic energy (TKE), Reynolds stresses, and vorticity information were measured to perform a comparison with the design condition. The time-averaged velocity contours indicated that the ballast and design conditions have distinct hook-like axial velocity contours; however, they appeared at different positions. The big difference under the ballast condition is that the top of the propeller disk area is near the free surface and a region with strong root mean square velocity fluctuation is formed near the free surface. The TKE, the Reynolds stresses, and the hub cap vortex (Hcv) are all affected by the turbulent velocity fluctuation region under the ballast condition. A strong bilge vortex (Bv) is produced when the water flows through the U-shaped stern for the design and ballast conditions.

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Gunes, Hasan, and Ulrich Rist. "Spatial resolution enhancement/smoothing of stereo–particle-image-velocimetry data using proper-orthogonal-decomposition–based and Kriging interpolation methods." Physics of Fluids 19, no. 6 (June 2007): 064101. http://dx.doi.org/10.1063/1.2740710.

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Wan-zhen, Luo, Guo Chun-yu, Wu Tie-cheng, Xu Pei, and Su Yu-min. "Experimental study on the wake fields of a ship attached with model ice based on stereo particle image velocimetry." Ocean Engineering 164 (September 2018): 661–71. http://dx.doi.org/10.1016/j.oceaneng.2018.07.014.

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Mullin, John A., and Werner J. A. Dahm. "Dual-plane stereo particle image velocimetry measurements of velocity gradient tensor fields in turbulent shear flow. I. Accuracy assessments." Physics of Fluids 18, no. 3 (March 2006): 035101. http://dx.doi.org/10.1063/1.2166447.

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Mullin, John A., and Werner J. A. Dahm. "Dual-plane stereo particle image velocimetry measurements of velocity gradient tensor fields in turbulent shear flow. II. Experimental results." Physics of Fluids 18, no. 3 (March 2006): 035102. http://dx.doi.org/10.1063/1.2166448.

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Nguyen, Thien Duy, John Craig Wells, and Chuong Vinh Nguyen. "Wall shear stress measurement of near-wall flow over inclined and curved boundaries by stereo interfacial particle image velocimetry." International Journal of Heat and Fluid Flow 31, no. 3 (June 2010): 442–49. http://dx.doi.org/10.1016/j.ijheatfluidflow.2009.12.002.

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Capone, Alessandro, Francisco Alves Pereira, Alessandro Maiocchi, and Fabio Di Felice. "Analysis of the hull wake of a twin-screw ship in steady drift by Borescope Stereo Particle Image Velocimetry." Applied Ocean Research 92 (November 2019): 101914. http://dx.doi.org/10.1016/j.apor.2019.101914.

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Cantrak, Djordje, James Heineck, Laura Kushner, and Novica Jankovic. "Turbulence investigation of the NASA common research model wing tip vortex." Thermal Science 21, suppl. 3 (2017): 851–62. http://dx.doi.org/10.2298/tsci161005328c.

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The paper presents high-speed stereo particle image velocimetry investigation of the NASA Common Research Model wing tip vortex. A three-percent scaled semi?span model, without nacelle and pylon, was tested in the 32- by 48-inch Indraft tunnel, at the Fluid Mechanics Laboratory at the NASA Ames Research Center. Turbulence investigation of the wing tip vortex is presented. Measurements of the wing-tip vortex were performed in a vertical cross-stream plane three tip-chords downstream of the wing tip trailing edge with a 2 kHz sampling rate. Experimental data are analyzed in the invariant anisotropy maps for three various angles of attack (0?, 2?, and 4?) and the same speed generated in the tunnel (V? = 50 m/s). This corresponds to a chord Reynolds number 2.68x105, where the chord length of 3? is considered the characteristic length. The region of interest was x = 220 mm and y = 90 mm. The 20 000 particle image velocimetry samples were acquired at each condition. Velocity fields and turbulence statistics are given for all cases, as well as turbulence structure in the light of the invariant theory. Prediction of the wing tip vortices is still a challenge for the computational fluid dynamics codes due to significant pressure and velocity gradients.

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Mullin, John A., and Werner J. A. Dahm. "Dual-plane stereo particle image velocimetry (DSPIV) for measuring velocity gradient fields at intermediate and small scales of turbulent flows." Experiments in Fluids 38, no. 2 (December 22, 2004): 185–96. http://dx.doi.org/10.1007/s00348-004-0898-8.

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