Relevant bibliographies by topics / Streamwise vortex

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  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers
  6. Reports

Academic literature on the topic 'Streamwise vortex'

Author: Grafiati
Published: 4 June 2021
Last updated: 11 February 2022

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Journal articles on the topic "Streamwise vortex"

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Doerffer, Piotr, Pawel Flaszynski, and Franco Magagnato. "Streamwise vortex interaction with a horseshoe vortex." Journal of Thermal Science 12, no. 4 (November 2003): 304–9. http://dx.doi.org/10.1007/s11630-003-0035-7.

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Hamilton, James M., and Frederick H. Abernathy. "Streamwise vortices and transition to turbulence." Journal of Fluid Mechanics 264 (April 10, 1994): 185–212. http://dx.doi.org/10.1017/s0022112094000637.

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A series of experiments was conducted to determine the conditions under which streamwise vortices can cause transition to turbulence in shear flows. A specially designed obstacle was used to produce a single vortex in a water-table flow, and the design of this obstacle is discussed. Laser-Doppler velocimetry measurements of the streamwise and crossflow velocity fields were made in transitional and non-transitional flows, and flow visualization was also used. It was found that strong vortices (vortices with large circulation) lead to turbulence while weaker vortices do not. Determination of a critical value of vortex strength for transition, however, was complicated by ambiguities in calculating the vortex circulation. The profiles of streamwise velocity were found to be inflexional for both transitional and non-transitional flows. Transition in single-vortex and multi-vortex flows was compared, and no qualitative differences were observed, suggesting no significant vortex interactions affecting transition.
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McKenna, C., M. Bross, and D. Rockwell. "Structure of a streamwise-oriented vortex incident upon a wing." Journal of Fluid Mechanics 816 (March 6, 2017): 306–30. http://dx.doi.org/10.1017/jfm.2017.87.

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Impingement of a streamwise-oriented vortex upon a fin, tail, blade or wing represents a fundamental class of flow–structure interaction that extends across a range of applications. It can give rise to unsteady loading known as buffeting and to changes of the lift to drag ratio. These consequences are sensitive to parameters of the incident vortex as well as the location of vortex impingement on the downstream aerodynamic surface, generically designated as a wing. Particle image velocimetry is employed to determine patterns of velocity and vorticity on successive cross-flow planes along the vortex, which lead to volume representations and thereby characterization of the streamwise evolution of the vortex structure as it approaches the downstream wing. This evolution of the incident vortex is affected by the upstream influence of the downstream wing, and is highly dependent on the spanwise location of vortex impingement. Even at spanwise locations of impingement well outboard of the wing tip, a substantial influence on the structure of the incident vortex at locations significantly upstream of the leading edge of the wing was observed. For spanwise locations close to or intersecting the vortex core, the effects of upstream influence of the wing on the vortex are to: decrease the swirl ratio; increase the streamwise velocity deficit; decrease the streamwise vorticity; increase the azimuthal vorticity; increase the upwash; decrease the downwash; and increase the root-mean-square fluctuations of both streamwise velocity and vorticity. The interrelationship between these effects is addressed, including the rapid attenuation of axial vorticity in presence of an enhanced defect of axial velocity in the central region of the vortex. When the incident vortex is aligned with, or inboard of, the tip of the wing, the swirl ratio decreases to values associated with instability of the vortex, thereby giving rise to enhanced values of azimuthal vorticity relative to the streamwise (axial) vorticity, as well as relatively large root-mean-square values of streamwise velocity and vorticity.
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Namgyal, Lhendup, and Joseph W. Hall. "Coherent Streamwise Vortex Structure of a Three-Dimensional Wall Jet." Fluids 6, no. 1 (January 11, 2021): 35. http://dx.doi.org/10.3390/fluids6010035.

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The dynamics of the coherent structures in a turbulent three-dimensional wall jet with an exit Reynolds number of 250,000 were investigated using the Snapshot Proper Orthogonal Decomposition (POD). A low-dimensional reconstruction using the first 10 POD modes indicates that the turbulent flow is dominated by streamwise vortex structures that grow in size and relative strength, and that are often accompanied by strong lateral sweeps of fluid across the wall. This causes an increase in the bulging and distortions of streamwise velocity contours as the flow evolves downstream. The instantaneous streamwise vorticity computed from the reconstructed instantaneous velocities has a high level of vorticity associated with these outer streamwise vortex structures, but often has a persistent pair of counter-rotating regions located close to the wall on either side of the jet centerline. A model of the coherent structures in the wall jet is presented. In this model, streamwise vortex structures are produced in the near-field by the breakdown of vortex rings formed at the jet outlet. Separate structures are associated with the near-wall streamwise vorticity. As the flow evolves downstream, the inner near-wall structures tilt outward, while the outer streamwise structures amalgamate to form larger streamwise asymmetric structures. In all cases, these streamwise vortex structures tend to cause large lateral velocity sweeps in the intermediate and far-field regions of the three-dimensional wall jet. Further, these structures meander laterally across the jet, causing a strongly intermittent jet flow.
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Namgyal, Lhendup, and Joseph W. Hall. "Coherent Streamwise Vortex Structure of a Three-Dimensional Wall Jet." Fluids 6, no. 1 (January 11, 2021): 35. http://dx.doi.org/10.3390/fluids6010035.

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The dynamics of the coherent structures in a turbulent three-dimensional wall jet with an exit Reynolds number of 250,000 were investigated using the Snapshot Proper Orthogonal Decomposition (POD). A low-dimensional reconstruction using the first 10 POD modes indicates that the turbulent flow is dominated by streamwise vortex structures that grow in size and relative strength, and that are often accompanied by strong lateral sweeps of fluid across the wall. This causes an increase in the bulging and distortions of streamwise velocity contours as the flow evolves downstream. The instantaneous streamwise vorticity computed from the reconstructed instantaneous velocities has a high level of vorticity associated with these outer streamwise vortex structures, but often has a persistent pair of counter-rotating regions located close to the wall on either side of the jet centerline. A model of the coherent structures in the wall jet is presented. In this model, streamwise vortex structures are produced in the near-field by the breakdown of vortex rings formed at the jet outlet. Separate structures are associated with the near-wall streamwise vorticity. As the flow evolves downstream, the inner near-wall structures tilt outward, while the outer streamwise structures amalgamate to form larger streamwise asymmetric structures. In all cases, these streamwise vortex structures tend to cause large lateral velocity sweeps in the intermediate and far-field regions of the three-dimensional wall jet. Further, these structures meander laterally across the jet, causing a strongly intermittent jet flow.
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Carlson, Bailey, Al Habib Ullah, and Jordi Estevadeordal. "Experimental Investigation of Vortex-Tube Streamwise-Vorticity Characteristics and Interaction Effects with a Finite-Aspect-Ratio Wing." Fluids 5, no. 3 (July 24, 2020): 122. http://dx.doi.org/10.3390/fluids5030122.

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An experimental study is conducted to analyze a streamwise-oriented vortex and investigate the unsteady interaction with a finite-aspect-ratio wing. A pressurized vortex tube is used to generate streamwise vortices in a wind tunnel and the resulting flow behavior is analyzed. The vortex tube, operated at various pressures, yields flows that evolve downstream under several freestream wind tunnel speeds. Flow measurements are performed using two- and three- dimensional (2D and 3D) particle image velocimetry to observe vortices and their freestream interactions from which velocity and vorticity data are comparatively analyzed. Results indicate that vortex velocity greater than freestream flow velocity is a primary factor in maintaining vortex structures further downstream, while increased supply pressure and reduced freestream velocity also reduce vortex dissipation rate. The generated streamwise-oriented vortex is also impinged on a finite-aspect-ratio airfoil wing with a cross-section of standard NACA0012 airfoil. The wingtip-aligned vortex is shown to investigate the interaction of the streamwise vortex and the wingtip vortex region. The results indicate that the vorticity at the high vortex-tube pressure has a significant effect on the boundary layer of airfoil.
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Younis, Md Yamin, Hua Zhang, Reiwei Zhu, and Zaka Muhammad. "Horseshoe Vortex Control Using Streamwise Vortices." Procedia Engineering 126 (2015): 139–44. http://dx.doi.org/10.1016/j.proeng.2015.11.196.

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Hiejima, Toshihiko. "Streamwise vortex breakdown in supersonic flows." Physics of Fluids 29, no. 5 (May 2017): 054102. http://dx.doi.org/10.1063/1.4982901.

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SZWABA, Ryszard, Pawel FLASZYNSKI, and Piotr DOERFFER. "Streamwise vortex generation by the rod." Chinese Journal of Aeronautics 32, no. 8 (August 2019): 1903–11. http://dx.doi.org/10.1016/j.cja.2019.03.033.

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Yaras, M. I. "Measurements of Surface-Roughness Effects on the Development of a Vortex Produced by an Inclined Jet in Cross-Flow." Journal of Fluids Engineering 126, no. 3 (May 1, 2004): 346–54. http://dx.doi.org/10.1115/1.1758260.

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This study examines the effects of surface roughness on the streamwise development of a vortex created by an isolated circular jet injected at 45 deg pitch and 90 deg skew into a crossflow. The study is motivated by the typical surface conditions encountered on in-service turbine blades of gas-turbine engines. Detailed measurements of the velocity field have been performed with a miniature four-wire probe at the jet exit plane, in the oncoming cross-stream boundary layer, and in a series of planes that capture the streamwise development of the vortex in the crossflow boundary layer up to about 15 jet-discharge diameters downstream of the jet. The paper presents the effects of surface roughness on the structure of the dominant streamwise vortex created by the interaction of the inclined jet with the mainstream, and documents the changes in the location, streamwise rate of change of circulation, and streamwise rate of diffusion of this vortex. Through these results, the change in the effectiveness of the vortex in energizing the boundary layer in the presence of surface roughness can be quantified.
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Dissertations / Theses on the topic "Streamwise vortex"

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Carlson, Bailey McKay. "Generation and Analysis of Streamwise Vortices from Vortex Tube Apparatus." Thesis, North Dakota State University, 2020. https://hdl.handle.net/10365/31783.

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A pressurized vortex tube is used to generate streamwise vortices in a wind tunnel and the resulting flow behavior is analyzed. The apparatus is intended to verify computational data from the AFRL by offering a method of conducting real-world counterpart experiments. The apparatus design process and other considered approaches are discussed. The vortex tube is operated at pressures of 20, 30 and 40 psi while the wind tunnel is operated at 3, 5, 10 and 20% capacity. Flow measurements are performed using particle image velocimetry to observe vortices and freestream interactions from which velocity and vorticity data is comparatively analyzed. Results indicate that vortex velocity greater than freestream flow velocity is a primary factor in maintaining vortex structures further downstream, while increased supply pressure and reduced freestream velocity also reduce vortex dissipation rate. A brief analysis of the vortex interaction with a downstream airfoil is presented to support future work.
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Connelly, Jonathan S. "Streamwise fluctuations of vortex breakdown at high Reynolds numbers." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2006. http://library.nps.navy.mil/uhtbin/hyperion/06Jun%5FConnelly.pdf.

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Cagney, N. "Vortex-induced vibrations of a cylinder in the streamwise direction." Thesis, University College London (University of London), 2013. http://discovery.ucl.ac.uk/1394192/.

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Vortex-induced vibration (VIV) of a circular cylinder has been the focus of extensive research, as it can lead to fatigue damage in a wide range of industrial applications. When the forces induced by the periodic shedding of vortices from a structure in crossflow coincide with one of its natural frequencies, the structure can exhibit large amplitude vibrations. The majority of the work performed in this area has focused exclusively on transverse vibration, while relatively little is known about VIV acting in the streamwise (flow) direction, although this is known to have a strong effect on the overall response of structures with multiple degrees-of-freedom (DOFs). This work aims to characterise the behaviour of the wake and the structural response of a cylinder throughout the streamwise VIV response regime, which is crucial if the wealth of information on the transverse-only case is to be extended to the more practical and complex case of multi-DOF structures. Experiments were performed on a cylinder free to move in the streamwise direction for a range of reduced velocities in a closed-loop water tunnel. Particle-Image Velocimetry (PIV) was used to simultaneously measure the cylinder displacement and the velocity field in the wake, in the Reynolds number range 400 - 5500. The response regime was characterised by two branches, separated by a region of low amplitude vibration, as reported in the literature. Five distinct regions were identified, each of which was discussed in terms of the dominant wake mode, structural response characteristics, velocity profiles and estimates of the strength and trajectories of the shed vortices. In the first branch the wake was found to switch intermittently between the symmetric S-I mode (in which two vortices were shed simultaneously from either side of the cylinder) and the alternate A-II mode (which is similar to the von Karman vortex street observed behind stationary bodies). A criterion was developed which could determine which mode was dominant in a given instantaneous PIV field, and the effect of both modes on the cylinder response and wake characteristics was examined. Multi-modal behaviour was also observed in the second branch. At one value of reduced velocity, the wake could exhibit one of three modes; the A-II, the SA (similar to the A-II mode, with the vortices forming closer to the cylinder base) or the A-IV mode (which was characterised by the shedding of two pairs of counter-rotating vortices). Each mode was associated with a different cylinder response amplitude. The stability of the cylinder response while each mode dominated was examined using phase-portraits, which indicated that the system behaved as a hard oscillator. The forces acting on the cylinder were estimated using two methods, based on the measurements of the cylinder displacement signal and the flow field, respectively. The results found using both methods were in agreement, and the accuracy of the estimates was discussed. It was found that the amplitude of the unsteady drag force was very low between the two response branches, which was thought to be the cause of the reduction in the cylinder vibrations in this region. Finally, the effect of the various wake modes on the amplitude of the fluid forces throughout the response regime was examined. The results presented in this study provide a comprehensive description of the behaviour of the wake and the associated fluid forces throughout the streamwise response regime. The work reveals the inherent differences between the extensively studied case of transverse-only VIV and the streamwise-only case, which is crucial if the wealth of information available on transverse VIV is to be extended to the more practical multi-DOF case.
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Barnes, Caleb J. "Unsteady Physics and Aeroelastic Response of Streamwise Vortex-Surface Interactions." Wright State University / OhioLINK, 2015. http://rave.ohiolink.edu/etdc/view?acc_num=wright1431937866.

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Benton, Stuart Ira. "Capitalizing on Convective Instabilities in a Streamwise Vortex-Wall Interaction." The Ohio State University, 2015. http://rave.ohiolink.edu/etdc/view?acc_num=osu1437664298.

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Qiu, Yuan J. "A study of streamwise vortex enhanced mixing in lobed mixer devices." Thesis, Massachusetts Institute of Technology, 1992. http://hdl.handle.net/1721.1/37175.

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Wendt, Bruce James. "The structure and development of streamwise vortex arrays embedded in a turbulent boundary layer." Case Western Reserve University School of Graduate Studies / OhioLINK, 1991. http://rave.ohiolink.edu/etdc/view?acc_num=case1055794234.

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Rullan, Jose Miguel. "The Aerodynamics of Low Sweep Delta Wings." Diss., Virginia Tech, 2008. http://hdl.handle.net/10919/29386.

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The aerodynamics of wings with moderately swept wings continues to be a challenging and important problem due to the current and future use in military aircraft. And yet, there is very little work devoted to the understanding of the aerodynamics of such wings. The problem is that such wings may be able to sustain attached flow next to broken-down delta-wing vortices, or stall like two-dimensional wings, while shedding vortices with generators parallel to their leading edge. To address this situation we studied the flow field over diamond-shaped planforms and sharp-edged finite wings. Possible mechanisms for flow control were identified and tested. We explored the aerodynamics of swept leading edges with no control. We presented velocity and vorticity distributions along planes normal and parallel to the free stream for wings with diamond shaped planform and sharp leading edges. We also presented pressure distributions over the suction side of the wing. Results indicated that in the inboard part of the wing, an attached vortex can be sustained, reminiscent of delta-wing type of a tip vortex, but further in the outboard region 2-D stall dominated even at 13° AOA and total stall at 21° AOA. To explore the unsteady flow field and the effectiveness of leading-edge control of the flow over a diamond-planform wing at 13° AOA, we employed Particle Image Velocimetry (PIV) at a Reynolds number of 43,000 in a water tunnel. Our results indicated that two-D-like vortices were periodically generated and shed. At the same time, an underline feature of the flow, a leading edge vortex was periodically activated, penetrating the separated flow, eventually emerging downstream of the trailing edge of the wing. To study the motion and its control at higher Reynolds numbers, namely 1.3 x 106 we conducted experiments in a wind tunnel. Three control mechanisms were employed, an oscillating mini-flap, a pulsed jet and spanwise continuous blowing. A finite wing with parallel leading and trailing edges and a rectangular tip was swept by 0°, 20°, and 40° and the pulsed jet employed as is control mechanism. A wing with a diamond-shaped-planform, with a leading edge sweep of 42°, was tested with the mini-flap. Surface pressure distributions were obtained and the control flow results were contrasted with the no-control cases. Our results indicated flow control was very effective at 20° sweep, but less so at 40° or 42°. It was found that steady spanwise blowing is much more effective at the higher sweep angle.
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Gunasekaran, Sidaard. "Relationship Between the Free Shear Layer, the Wingtip Vortex and Aerodynamic Efficiency." University of Dayton / OhioLINK, 2016. http://rave.ohiolink.edu/etdc/view?acc_num=dayton1470231642.

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Fassmann, Wesley N. "An Experimental Study of Bio-Inspired Force Generation by Unsteady Flow Features." BYU ScholarsArchive, 2014. https://scholarsarchive.byu.edu/etd/5316.

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As the understanding of the workings of the biological world expands, biomimetic designs increasingly move into the focus of engineering research studies. For this thesis, two studiesinvolving leading edge vortex generation for lift production as observed in nature were explored intheir respective flow regimes. The first study focused on the steady state analysis of streamwise vortices generated byleading edge tubercles of an adult humpback whale flipper. A realistic scaled model of a humpbackflipper was fabricated based on the 3D reconstruction from a sequence of 18 images taken whilecircumscribing an excised flipper of a beached humpback whale. Two complementary modelswith smooth leading edges were transformed from this original digitized model and fabricatedfor testing to further understand the effect of the leading edge tubercles. Experimentally-obtainedforce and qualitative flow measurements were used to study the influence of the leading edgetubercles. The presence of leading edge tubercles are shown to decrease maximum lift coefficient(Cl ), but increase Cl production in the post-stall region. By evaluating a measure of hydrodynamicefficiency, humpback whale flipper geometry is shown to be more efficient in the pre-stall regionand less efficient in the post-stall region as compared to a comparable model with a smooth leadingedge. With respect to a humpback whale, if the decrease in efficiency during post-stall angles ofattack was only required during short periods of time (turning), then this decrease in efficiencymay not have a significant impact on the lift production and energy needs. For the pursuit ofbiomimetic designs, this decrease in efficiency could have potential significance and should beinvestigated further. Qualitative flow measurements further demonstrate that these force results aredue to a delay of separation resulting from the presence of tubercles.The second study investigated explored the effects of flapping frequency on the passive flowcontrol of a flapping wing with a sinusoidal leading edge profile. At a flapping frequency of f =0.05 Hz, an alternating streamwise vortical formation was observed for the sinusoidal leading edge,while a single pair of vortices were present for the straight leading edge. A sinusoidal leading edgecan be used to minimize spanwise flow by the generation of the observed alternating streamwisevortices. An increase in flapping frequency results in these streamwise vortices becoming stretchedin the path of the wing. The streamwise vortices are shown to minimize spanwise flow even afterbeing stretched. Once instabilities are formed at f ≥ 0:1 Hz due to velocity shearing generatedby the increase in cross-radial velocity, the alternating streamwise vortices begin to break downresulting in a increase of spanwise flow.
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Books on the topic "Streamwise vortex"

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Joseph, Mathew, and United States. National Aeronautics and Space Administration., eds. The development of a mixing layer under the action of weak streamwise vortices. [Washington, DC: National Aeronautics and Space Administration, 1993.

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Isaac, Greber, Hingst Warren R, and United States. National Aeronautics and Space Administration., eds. The structure and development of streamwise vortex arrays embedded in a turbulent boundary layer. [Washington, DC]: National Aeronautics and Space Administration, 1991.

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Isaac, Greber, Hingst Warren R, and United States. National Aeronautics and Space Administration., eds. The structure and development of streamwise vortex arrays embedded in a turbulent boundary layer. [Washington, DC]: National Aeronautics and Space Administration, 1991.

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Book chapters on the topic "Streamwise vortex"

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He, Changjiang, Zhongdong Duan, and Jinping Ou. "Analyses on Vortex-Induced Vibration with Consideration of Streamwise Degree of Freedom." In Computational Structural Engineering, 383–89. Dordrecht: Springer Netherlands, 2009. http://dx.doi.org/10.1007/978-90-481-2822-8_42.

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Westphal, R. V., J. K. Eaton, and W. R. Pauley. "Interaction Between a Vortex and a Turbulent Boundary Layer in a Streamwise Pressure Gradient." In Turbulent Shear Flows 5, 266–77. Berlin, Heidelberg: Springer Berlin Heidelberg, 1987. http://dx.doi.org/10.1007/978-3-642-71435-1_22.

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Adaramola, M. S., D. Sumner, and D. J. Bergstrom. "Effect of Velocity Ratio on the Streamwise Vortex Structures in the Wake of a Stack." In IUTAM Symposium on Unsteady Separated Flows and their Control, 477–86. Dordrecht: Springer Netherlands, 2009. http://dx.doi.org/10.1007/978-1-4020-9898-7_41.

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Kaykayoglu, C. Ruhi. "Vortex Method Simulation of the Wake from a Rigid Cylinder at Re = 200 Subjected to Streamwise Amplitude-Modulated Flow Excitation." In Bluff-Body Wakes, Dynamics and Instabilities, 253–56. Berlin, Heidelberg: Springer Berlin Heidelberg, 1993. http://dx.doi.org/10.1007/978-3-662-00414-2_56.

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Tang, G., L. Cheng, L. Lu, M. Zhao, F. Tong, and G. Dong. "Vortex Formation in the Wake of a Streamwisely Oscillating Cylinder in Steady Flow." In Fluid-Structure-Sound Interactions and Control, 429–34. Berlin, Heidelberg: Springer Berlin Heidelberg, 2015. http://dx.doi.org/10.1007/978-3-662-48868-3_68.

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Conference papers on the topic "Streamwise vortex"

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Forster, Kyle J., Tracie Barber, Sammy Diasinos, and Graham Doig. "Numerical Investigation of Streamwise Vortex Interaction." In SAE 2015 AeroTech Congress & Exhibition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 2015. http://dx.doi.org/10.4271/2015-01-2573.

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Garmann, Daniel J., and Miguel R. Visbal. "Streamwise-oriented vortex interactions with a NACA0012 wing." In 53rd AIAA Aerospace Sciences Meeting. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2015. http://dx.doi.org/10.2514/6.2015-1066.

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LEBOEUF, RICHARD, and RABINDRA MEHTA. "Streamwise vortex meander in a plane mixing layer." In 31st Aerospace Sciences Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1993. http://dx.doi.org/10.2514/6.1993-553.

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Garmann, Daniel J., and Miguel R. Visbal. "Interaction of a streamwise-oriented vortex with a wing." In 52nd Aerospace Sciences Meeting. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2014. http://dx.doi.org/10.2514/6.2014-1282.

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BELL, JAMES, and RABINDRA MEHTA. "A streamwise vortex embedded in a plane mixing layer." In 1st National Fluid Dynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1988. http://dx.doi.org/10.2514/6.1988-3606.

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Barnes, Caleb J., Miguel R. Visbal, and George P. Huang. "Numerical Simulations of Streamwise-Oriented Vortex/Flexible Wing Interactions." In 44th AIAA Fluid Dynamics Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2014. http://dx.doi.org/10.2514/6.2014-2313.

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SARPKAYA, T., and D. NEUBERT. "Interaction of a streamwise vortex with a free surface." In 31st Aerospace Sciences Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1993. http://dx.doi.org/10.2514/6.1993-556.

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Wicks, Michael, Flint Thomas, David Schatzman, Patrick Bowles, Thomas Corke, Mehul Patel, and Alan Cain. "A Parametric Investigation of Plasma Streamwise Vortex Generator Performance." In 50th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2012. http://dx.doi.org/10.2514/6.2012-824.

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Zhang, Xin, and Hui-Liu Zhang. "Some aspects of streamwise vortex production using air jets." In 34th Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1996. http://dx.doi.org/10.2514/6.1996-209.

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Barnes, Caleb J., Miguel R. Visbal, and Raymond E. Gordnier. "Investigation of aeroelastic effects in streamwise-oriented vortex/wing interactions." In 52nd Aerospace Sciences Meeting. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2014. http://dx.doi.org/10.2514/6.2014-1281.

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Reports on the topic "Streamwise vortex"

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Freymuth, P., R. Tarasewicz, and W. Bank. Vortex Patterns Behind Airfoils in Streamwise Oscillation. Fort Belvoir, VA: Defense Technical Information Center, November 1989. http://dx.doi.org/10.21236/ada229883.

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