Relevant bibliographies by topics / Wingtip Vortices

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Academic literature on the topic 'Wingtip Vortices'

Author: Grafiati
Published: 4 June 2021
Last updated: 1 February 2022

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Journal articles on the topic "Wingtip Vortices"

1

Zhang, M., Y. K. Wang, and S. Fu. "Generation Mechanism and Reduction Method of Induced Drag Produced by Interacting Wingtip Vortex System." Journal of Mechanics 34, no. 2 (September 14, 2017): 231–41. http://dx.doi.org/10.1017/jmech.2017.76.

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AbstractThe formation and evolution of wingtip vortex system generated from three wing configurations are simulated with the improved delayed detached eddy simulation (IDDES) method. Numerical results show that each layout produces an interacting wingtip vortex system. These three corresponding vortical interactions are, respectively, the interaction between wingtip vortex and its counter-rotating vortex, winglet-tip vortex, and winglet four-vortex system. The fluid entrainment of ambient fluid and vortical impulse transport resulted from inductive effect have been founded generally existing in its formation and evolution. These two dominated mechanisms account for induced drag generation. On one hand, the winglet with toed-out angle is considered capable of changing the flow field around the winglet, and decomposing the winglet-tip vortex into four small vortices. Due to quite few fluid entrainment effects, this typical four-vortex system that cannot merge and only dissipate in the near wake scarcely contributes to the induced drag. On the other hand, a potential drag reduction method is also indicated that a lower induced drag can be obtained when the merger of wingtip and winglet-tip vortex is controlled and eliminated. This investigation will offer a novel perspective to guide the design of wingtip device and method of crusing resistance reduction for aircrafts.
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2

Marshall, R. E., and T. J. Myers. "Wingtip generated wake vortices as radar target." IEEE Aerospace and Electronic Systems Magazine 11, no. 12 (1996): 27–30. http://dx.doi.org/10.1109/62.544796.

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3

Liu, Y. C., and F. B. Hsiao. "Aerodynamic Investigations of Low-Aspect-Ratio Thin Plate Wings at Low Reynolds Numbers." Journal of Mechanics 28, no. 1 (March 2012): 77–89. http://dx.doi.org/10.1017/jmech.2012.8.

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ABSTRACTTo realize the relationship between flow structures of wingtip vortices and post stall characteristics of low aspect-ratio wings, this paper experimentally studies the aerodynamic characteristics and the corresponding flow structures of the rectangular thin-plate wings at Reynolds numbers between 104 and 105. The aerodynamic properties to be studied include lift, drag, slopes at linear and nonlinear range of the lift curves and lift-to-drag ratios of the tested wings with the aspect ratio varying from 1.0 to 3.0. The flow structures regarding the leading-edge separation vortices and wingtip vortices at upper surface and near-wake regions of the wings are also investigated by smoke-wire visualization. Results indicate that the high stall angle of attack and vortex lift are clearly manifested to induce the nonlinear increase in the lift curves as the aspect ratio reaches less than 1.6. This phenomenon is specifically observed to augment the aerodynamic properties with the decrease of the aspect ratio. Additionally, the corresponding flow visualization also indicates that the wingtip vortices and the areas of highly affected regions are duly increased with the increase of the angle of attack up to 40°, which makes certain that the extra increase of the nonlinear lift results from these vortices. This result can be practically applied to the planform design for unmanned aerial vehicles.
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Kasmai, N., D. Thompson, E. Luke, M. Jankun-Kelly, and R. Machiraju. "Feature-based adaptive mesh refinement for wingtip vortices." International Journal for Numerical Methods in Fluids 66, no. 10 (March 23, 2010): 1274–94. http://dx.doi.org/10.1002/fld.2312.

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5

Zaccara, Mirko, Gerardo Paolillo, Carlo Salvatore Greco, Tommaso Astarita, and Gennaro Cardone. "Flow control of wingtip vortices through synthetic jets." Experimental Thermal and Fluid Science 130 (January 2022): 110489. http://dx.doi.org/10.1016/j.expthermflusci.2021.110489.

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6

Liu, Zhi Rong, Jun Wei Wang, and Rui Zhu. "Fluid Experimental Research on Dual-Vortex Interaction Instability." Advanced Materials Research 459 (January 2012): 195–98. http://dx.doi.org/10.4028/www.scientific.net/amr.459.195.

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A series of dual-vortex fulid visualization and interaction instability experiments are undertaken with PIV (Particle Image Velocimetry) system under various experimental parameters sets. The motion characteristics and the circulation-time curves of the dual-vortex are presented through PIV processing and analysis. The dual-vortex distance b=50mm, main wingtip angle α1=10° & side wingtip angle α2=8° are optimum experimental parameters for vortices dissipation, the most vortex strength is reduced by 30%-40%
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Barber, T., and P. Kurts. "Downstream evolution of wingtip vortices produced from an inverted wing." Aeronautical Journal 119, no. 1216 (June 2015): 747–63. http://dx.doi.org/10.1017/s0001924000010800.

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AbstractCounter-rotating vortices form from the opposite edges of lifting surfaces, and gradually move laterally and dissipate as they travel downstream (as seen in a wing-fixed reference frame). Under ground effect conditions, the vortex from a lifting wing – such as that used in an aircraft application – moves laterally outboard from the wingtip as it progresses downstream; for a downforce wing in ground effect – such as that used in an automotive application – the vortex moves laterally inboard. An interesting case is the situation where the inboard moving vortices become in close proximity to each other. The objective of the present study was to investigate counter-rotating vortices produced from a low aspect ratio downforce wing operating in ground effect. The pair of vortices move towards each other and mutually induce an upwards directed motion which in turn reduces the inboard movement driven by the ground effect. Experimental data gained from three-dimensional Laser Doppler Anemometry in a moving ground wind-tunnel was used to validate a Large Eddy Simulation computational result.
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Henningsson, P., F. T. Muijres, and A. Hedenström. "Time-resolved vortex wake of a common swift flying over a range of flight speeds." Journal of The Royal Society Interface 8, no. 59 (December 3, 2010): 807–16. http://dx.doi.org/10.1098/rsif.2010.0533.

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The wake of a freely flying common swift ( Apus apus L.) is examined in a wind tunnel at three different flight speeds, 5.7, 7.7 and 9.9 m s −1 . The wake of the bird is visualized using high-speed stereo digital particle image velocimetry (DPIV). Wake images are recorded in the transverse plane, perpendicular to the airflow. The wake of a swift has been studied previously using DPIV and recording wake images in the longitudinal plane, parallel to the airflow. The high-speed DPIV system allows for time-resolved wake sampling and the result shows features that were not discovered in the previous study, but there was approximately a 40 per cent vertical force deficit. As the earlier study also revealed, a pair of wingtip vortices are trailing behind the wingtips, but in addition, a pair of tail vortices and a pair of ‘wing root vortices’ are found that appear to originate from the wing/body junction. The existence of wing root vortices suggests that the two wings are not acting as a single wing, but are to some extent aerodynamically detached from each other. It is proposed that this is due to the body disrupting the lift distribution over the wing by generating less lift than the wings.
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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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Inasawa, Ayumu, Fumihide Mori, and Masahito Asai. "Detailed Observations of Interactions of Wingtip Vortices in Close-Formation Flight." Journal of Aircraft 49, no. 1 (January 2012): 206–13. http://dx.doi.org/10.2514/1.c031480.

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Dissertations / Theses on the topic "Wingtip Vortices"

1

Giuni, Michea. "Formation and early development of wingtip vortices." Thesis, University of Glasgow, 2013. http://theses.gla.ac.uk/3871/.

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Wingtip vortices are extremely important phenomena in fluid dynamics for their negative effects in many applications. Despite the many studies on this particular flow, the current understanding is still poor in providing a form base for the design of effective tip geometry modifications and vortex control devices. A rectangular wing with squared and rounded wingtips was tested in order to identify the main mechanisms involved in the formation of the vortex on the wing and in its early development in the wake. The complementarity of a number of experimental techniques adopted, such as surface flow visualizations, wall pressure measurements, smoke visualizations and stereoscopic particle image velocimetry (SPIV), gave a richer insight of the physics and the basic mechanisms of the vortex development. Furthermore, a large number of configurations were tested exploring the effects of several parameters such as wing chord, aspect ratio, wingtip geometry, angle of attack and Reynolds number. The development of the vortex along the wing showed the formation of several secondary vortices which interacted with the primary vortex generating low frequency fluctuations. The structure of the flow at this stage was analysed introducing a compact description through characteristic lines of the vortex system defined from the velocity vector field in the vicinity of the wing surface. The high spatial resolution achieved by the SPIV arrangement allowed a deeper understanding of the vortex structure in the early wake and the turbulence production and dissipation within the vortex core. The relaminarization process of the vortex core promoted by centrifugal motion was observed. The relation between vortex meandering, turbulence, secondary vortices and wake sheet was discussed. A comparison of different methods for the averaging of instantaneous planar vector fields was performed showing the effects and importance of the meandering. An axial acceleration of the flow within the vortex was observed and the formation of different axial flow distributions was discussed. A minimum wake-like flow of 0.62 and a maximum jet-like flow of 1.7 times the freestream velocity were measured and a linear relation between a vortex circulation parameter and the axial velocity peak was found.
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2

Planchenault, Pascal, and Pascal Planchenault. "Modification of Wingtip Vortices using Pulsed and Steady Jets." Thesis, The University of Arizona, 2017. http://hdl.handle.net/10150/624126.

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Wingtip vortices, created as a byproduct of lift, are both a hazard and a significant limiting factor in the increase of air traffic. In order to reduce separation distances between airplanes and increase safety, active flow control solutions are considered, however, more research is required to better understand the behavior of wingtip vortices. Therefore, this research focuses on the modification of the flow structure downstream using pulsed jets, visualization of the behavior of wingtip vortices using two dimensional particle image velocimetry, as well as measurements of the forces and moments affected by the pulsed jets using an aerodynamic balance. A NACA 0012 wing model equipped with two slots was mounted in a wind tunnel at approximately 150,000 Reynolds number. A valve system was designed to create jets of air at the wing tip in a steady or pulsed pattern from a slot placed either on the pressure side or the suction side. Particle image velocimetry measurements were taken at various distances downstream, and post-processed for the characterization of the vortex : position, angle, distance, vorticity contour, and circulation. Results indicate that the vortex can be forced into a cyclic pattern constrained between the baseline (no jet) vortex core position, and the position when the jet is permanently activated (steady blowing cases). Depending on the slot used, the vortex trajectory can be forced into an inclination angle. Steady blowing cases show near-sinusoidal oscillations, while pulsed blowing cases exhibit a steady rise in angle, with a slight oscillating pattern in displacement distance values. The circulation values are significantly changed, with a significantly higher dispersion than for the baseline case. Furthermore, the vortex core size is consistently larger as it is displaced away from the baseline case. Additionally, lift, drag and pitching moment were measured in a wind tunnel using an aerodynamic balance. Results showed that lift/drag coefficients consistent with published results, and that activating the jets on the pressure or suction side decreased lift. As instability grows, the destruction of the wingtip vortices occurs past the maximum downstream distance studied, therefore, additional PIV measurements should be taken further downstream. Moreover, supplementary PIV measurements at the slot themselves should be considered to better understand how the perturbed flow structure interacts with the pulsed jets.
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3

Memon, Muhammad Omar. "Wingtip Vortices and Free Shear Layer Interaction in the Vicinity of Maximum Lift to Drag Ratio Lift Condition." University of Dayton / OhioLINK, 2017. http://rave.ohiolink.edu/etdc/view?acc_num=dayton1492701624726378.

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4

Pierson, Kristopher C. "Vorticity Confinement Applied to Induced Drag Prediction and the Simulation of Turbulent Wingtip Vortices from Fixed and Rotating Wing." University of Akron / OhioLINK, 2014. http://rave.ohiolink.edu/etdc/view?acc_num=akron1396881138.

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5

Fares, Ehab Mahmoud Aziz Mohamed [Verfasser]. "Numerical simulation of the interaction of wingtip vortices and engine jets in the near field / vorgelegt von Ehab Mahmoud Aziz Mohamed Fares." 2002. http://d-nb.info/966152360/34.

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Books on the topic "Wingtip Vortices"

1

E, Marshall Robert. Radar reflectivity in wingtip-generated wake vortices. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1997.

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2

E, Marshall Robert, Langley Research Center, Research Triangle Institute. Center for Aerospace Technology., and Virginia Polytechnic Institute and State University., eds. Three-centimeter Doppler radar observations of wingtip-generated wake vortices in clear air. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1997.

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3

An Object Oriented Simulation of the C-17 Wingtip Vortices in the Airdrop Environment. Storming Media, 1997.

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4

Greg, Zilliac, Bradshaw P. 1935-, and Ames Research Center, eds. Turbulence measurements in the near field of a wingtip vortex. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1997.

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Greg, Zilliac, Bradshaw P. 1935-, and Ames Research Center, eds. Turbulence measurements in the near field of a wingtip vortex. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1997.

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6

E, Marshall Robert, and Langley Research Center, eds. Three-centimeter Doppler radar observations of wingtip-generated wake vortices in clear air: Under contract NAS1-18925. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1997.

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E, Marshall Robert, and Langley Research Center, eds. Three-centimeter Doppler radar observations of wingtip-generated wake vortices in clear air: Under contract NAS1-18925. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1997.

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E, Marshall Robert, and Langley Research Center, eds. Three-centimeter Doppler radar observations of wingtip-generated wake vortices in clear air: Under contract NAS1-18925. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1997.

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E, Marshall Robert, and Langley Research Center, eds. Three-centimeter Doppler radar observations of wingtip-generated wake vortices in clear air: Under contract NAS1-18925. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1997.

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Conference papers on the topic "Wingtip Vortices"

1

Goparaju, Kalyan, and Mei Zhuang. "Numerical Simulation of Wingtip Vortices." In 30th AIAA Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2012. http://dx.doi.org/10.2514/6.2012-3328.

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2

Durbin, Paul, Xin Huang, Hui Hu, and Hirofumi Igarashi. "Wind Tunnel Effects on Wingtip Vortices." In 48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2010. http://dx.doi.org/10.2514/6.2010-325.

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3

Memon, Muhammad O., Kevin Wabick, Aaron Altman, and Rainer M. Buffo. "Wingtip Vortices from an Exergy-Based Perspective." In 52nd Aerospace Sciences Meeting. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2014. http://dx.doi.org/10.2514/6.2014-0955.

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Gerz, T., and F. Holzaepfel. "Wingtip vortices, turbulence, and the distribution of emissions." In 2nd AIAA, Theoretical Fluid Mechanics Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1998. http://dx.doi.org/10.2514/6.1998-2856.

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Guha, Tufan K., and Rajan Kumar. "Active Control of Wingtip Vortices using Piezoelectric Actuated Winglets." In 54th AIAA Aerospace Sciences Meeting. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2016. http://dx.doi.org/10.2514/6.2016-0323.

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Boling, Jeremy S., Gecheng Zha, and Aaron Altman. "Numerical Investigation of Wingtip Vortices of Coflow Jet Active Flow Control Wings." In AIAA AVIATION 2020 FORUM. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2020. http://dx.doi.org/10.2514/6.2020-2943.

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Bodling, Andrew L., and Daniel J. Garmann. "Wingtip Vortex Stability and Control Using Mean Flow Perturbation." In ASME-JSME-KSME 2019 8th Joint Fluids Engineering Conference. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/ajkfluids2019-5473.

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Abstract Wingtip vortices generated by aircraft are the source of induced drag. Therefore, flow control devices such as winglets have been created to reduce the impact of tip vortices and consequently improve the wings performance. To use other flow control devices such as periodic heat-flux sources, the receptivity to the actuator must be fully optimized to be effective. The optimization process includes actuator placement, frequency selection and spatial modulation. The Mean Flow Perturbation (MFP) technique is a linear stability analysis that can be used to understand the receptivity of base flows to small perturbations. Its advantage over other linear stability analyses is that it can be applied fairly easily to complex 3-D flows in a relatively efficient manner, embedded within traditional flow-solver frameworks. This technique can help in gaining a better understanding of the receptivity of a flow control actuator that is used to control a complex 3-D flow. The current study seeks to apply the MFP technique to the author’s previous work on unsteady tip vortices. The aspect-ratio-four, rounded-tip wing has a NACA0012 section and operates at a Reynolds number of Re = 2 × 105 and incidence of α = 12°. The objective is to uncover the least stable mode shapes and frequencies of the structure using MFP in hopes of informing future flow control design techniques. At these conditions, the MFP shows a dominant least stable frequency and mode shape that occurs near the trailing edge of the wingtip. A region near the incipient separation of the vortex also showed with a definitive spatial wavelength that may be susceptible to tailored control.
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Saneholtz, Nolan, Samantha A. Kasper, Tyler Burke, and Jude Rapski. "The Utilization of Wingtip Vortices in Formation Flight Aerodynamics for Unmanned Arial Vehicles." In AIAA Atmospheric Flight Mechanics Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2016. http://dx.doi.org/10.2514/6.2016-1285.

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Boling, Jeremy S., Gecheng Zha, and Aaron Altman. "Correction: Numerical Investigation of Wingtip Vortices of Coflow Jet Active Flow Control Wings." In AIAA AVIATION 2020 FORUM. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2020. http://dx.doi.org/10.2514/6.2020-2943.c1.

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Kolomenskiy, Dmitry, Roberto Paoli, and Jean-François Boussuge. "Hybrid RANS–LES Simulation of Wingtip Vortex Dynamics." In ASME 2014 4th Joint US-European Fluids Engineering Division Summer Meeting collocated with the ASME 2014 12th International Conference on Nanochannels, Microchannels, and Minichannels. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/fedsm2014-21349.

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This paper presents a feasibility study of a hybrid RANS–LES approach to numerical simulation of aircraft wing-tip vortices. A NACA 0012 wing is considered for which earlier published experimental and numerical data are available. Mesh sensitivity tests of our RANS solver and comparisons between two different turbulence models indicate that the RANS approach adequately describes the flow upstream from the trailing edge, but overestimates the rate of decay of the wing-tip vortex. A hybrid RANS–LES method is presented that results in a better agreement with the wind tunnel experiment, hence this approach is suggested for numerical simulation of the wake of an airliner.
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