Relevant bibliographies by topics / Plane Wake

Academic literature on the topic 'Plane Wake'

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Published: 10 December 2022
Last updated: 28 January 2023

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Journal articles on the topic "Plane Wake"

1

ROGERS, MICHAEL M. "The evolution of strained turbulent plane wakes." Journal of Fluid Mechanics 463 (July 25, 2002): 53–120. http://dx.doi.org/10.1017/s0022112002008686.

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Direct numerical simulations of ten turbulent time-evolving strained wakes have been generated using a pseudo-spectral numerical method. In all the simulations, the strain was applied to the same (previously generated) initial developed self-similar wake flow field. The cases include flows in which the wake is subjected to various orientations of the applied mean strain, including both plane and axisymmetric strain configurations. In addition, for one particular strain geometry, cases with differing strain rates were considered. Although classical self-similar analysis does yield a self-similar solution for strained wakes, this solution does not describe the observed flow evolution. Instead, the wake mean velocity profiles evolve according to a different ‘equilibrium similarity solution’, with the strained wake width being determined by the straining in the inhomogeneous cross-stream direction. Wakes that are compressed in this direction eventually exhibit constant widths, whereas wakes in cases with expansive cross-stream strain ultimately spread at the same rate as the distortion caused by the applied strain. The shape of the wake mean velocity deficit profile is nearly universal. Although the effect of the strain on the mean flow is pronounced and rapid, the response of the turbulence to the strain occurs more slowly. Changes in the turbulence intensity cannot keep pace with changes in the mean wake velocity deficit, even for relatively low strain rates.
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2

Weygandt, James H., and Rabindra D. Mehta. "Three-dimensional structure of straight and curved plane wakes." Journal of Fluid Mechanics 282 (January 10, 1995): 279–311. http://dx.doi.org/10.1017/s0022112095000140.

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The formation and evolution of the three-dimensional structure of straight and mildly curved ($b/\bar{R} < 2\%$) flat plate wakes at relatively high Reynolds numbers (Reb = 28 000) have been studied through detailed measurements of the mean and fluctuating velocities. In both cases, the role of initial conditions was examined by generating wakes from untripped (laminar) and tripped (turbulent) initial boundary layers. The curved wake was affected by the angular momentum instability such that the inside half of the wake was unstable, whereas the outside half was stable. In both the straight and curved untripped wakes, large spanwise variations, in the form of ‘pinches’ and ‘crests’, were observed in the contours of mean velocity and Reynolds stresses. Well-organized, ‘spatially stationary’ streamwise vorticity was generated in the near-field region in the form of quadrupoles, to which the spanwise variations in the velocity contours were attributed. The presence of mean streamwise vorticity had a significant effect on the wake growth and defect decay rates, mainly by providing additional entrainment. In the straight wake, the mean streamwise vorticity decayed on both sides of the wake such that it had decayed completely by the far-field region. However, in the curved case, the mean streamwise vorticity on the unstable side decayed at a rate significantly lower than that on the stable side. Despite the decay of mean streamwise vorticity, the spanwise variations persisted into the far wake in both cases. The effects of curvature were also apparent in the Reynolds stress results which showed that the levels on the unstable side were increased significantly compared to those on the stable side, with the effect much stronger in the initially laminar wake. With the initial boundary layers tripped, spatially stationary streamwise vortex structures were not observed in either the straight or curved wakes and the velocity contours appeared nominally two-dimensional. This result further confirms the strong dependency of the three-dimensional structure of plane wakes on initial conditions.
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TAMMISOLA, OUTI, FREDRIK LUNDELL, PHILIPP SCHLATTER, ARMIN WEHRFRITZ, and L. DANIEL SÖDERBERG. "Global linear and nonlinear stability of viscous confined plane wakes with co-flow." Journal of Fluid Mechanics 675 (April 4, 2011): 397–434. http://dx.doi.org/10.1017/jfm.2011.24.

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The global stability of confined uniform density wakes is studied numerically, using two-dimensional linear global modes and nonlinear direct numerical simulations. The wake inflow velocity is varied between different amounts of co-flow (base bleed). In accordance with previous studies, we find that the frequencies of both the most unstable linear and the saturated nonlinear global mode increase with confinement. For wake Reynolds numberRe= 100 we find the confinement to be stabilising, decreasing the growth rate of the linear and the saturation amplitude of the nonlinear modes. The dampening effect is connected to the streamwise development of the base flow, and decreases for more parallel flows at higherRe. The linear analysis reveals that the critical wake velocities are almost identical for unconfined and confined wakes atRe≈ 400. Further, the results are compared with literature data for an inviscid parallel wake. The confined wake is found to be more stable than its inviscid counterpart, whereas the unconfined wake is more unstable than the inviscid wake. The main reason for both is the base flow development. A detailed comparison of the linear and nonlinear results reveals that the most unstable linear global mode gives in all cases an excellent prediction of the initial nonlinear behaviour and therefore the stability boundary. However, the nonlinear saturated state is different, mainly for higherRe. ForRe= 100, the saturated frequency differs less than 5% from the linear frequency, and trends regarding confinement observed in the linear analysis are confirmed.
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CHEN, DAOYI, and GERHARD H. JIRKA. "Absolute and convective instabilities of plane turbulent wakes in a shallow water layer." Journal of Fluid Mechanics 338 (May 10, 1997): 157–72. http://dx.doi.org/10.1017/s0022112097005041.

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In shallow turbulent wake flows (typically an island wake), the flow patterns have been found experimentally to depend mainly on a shallow wake parameter, S=cfD/h in which cf is a quadratic-law friction coefficient, D is the island diameter and h is water depth. In order to understand the dependence of flow patterns on S, the shallow-water stability equation (a modified Orr–Sommerfeld equation) has been derived from the depth-averaged equations of motion with terms which describe bottom friction. Absolute and convective instabilities have been investigated on the basis of wake velocity profiles with a velocity deficit parameter R. Numerical computations have been carried out for a range of R-values and a stability diagram with two dividing lines was obtained, one defining the boundary between absolute and convective instabilities Sca, and another defining the transition between convectively unstable and stable wake flow Scc. The experimental measurements (Chen & Jirka 1995) of return velocities in shallow wakes were used to compute R-values and two critical values, SA=0.79 and SC=0.85, were obtained at the intersections with lines Sca and Scc. Through comparison with transition values observed experimentally for wakes with unsteady bubble (recirculation zone) and vortex shedding, SU and SV respectively, the sequence SC>SA> SU>SV shows vortex shedding to be the end product of absolute instability. This is analogous to the sequence of critical Reynolds numbers for an unbounded wake of large spanwise extent. Experimental frequency characteristics compare well with theoretical results. The observed values of SU and SV for different flow patterns correspond to the velocity profile with R=−0.945, which is located at the end of the wake bubble, and it provides the dominant mode.
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EWING, D., W. K. GEORGE, M. M. ROGERS, and R. D. MOSER. "Two-point similarity in temporally evolving plane wakes." Journal of Fluid Mechanics 577 (April 19, 2007): 287–307. http://dx.doi.org/10.1017/s0022112006003260.

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The governing equations for the two-point correlations of the turbulent fluctuating velocity in the temporally evolving wake were analysed to determine whether they could have equilibrium similarity solutions. It was found that these equations could have such solutions for a finite-Reynolds-number wake, where the two-point velocity correlations could be written as a product of a time-dependent scale and a function dependent only on similarity variables. It is therefore possible to collapse the two-point measures of all the scales of motions in the temporally evolving wake using a single set of similarity variables. As in an earlier single-point analysis, it was found that the governing equations for the equilibrium similarity solutions could not be reduced to a form that was independent of a growth-rate dependent parameter. Thus, there is not a single ‘universal’ solution that describes the state of the large-scale structures, so that the large-scale structures in the far field may depend on how the flow is generated.The predictions of the similarity analysis were compared to the data from two direct numerical simulations of the temporally evolving wakes examined previously. It was found that the two-point velocity spectra of these temporally evolving wakes collapsed reasonably well over the entire range of scales when they were scaled in the manner deduced from the equilibrium similarity analysis. Thus, actual flows do seem to evolve in a manner consistent with the equilibrium similarity solutions.
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6

Neu, W., P. Mitra, and J. Schetz. "The Wake of Self-Propelled and Over-Thrusted Slender Bodies Near a Simulated Free Surface." Journal of Ship Research 32, no. 01 (March 1, 1988): 70–79. http://dx.doi.org/10.5957/jsr.1988.32.1.70.

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Measurements were performed in the turbulent wake of a propeller-driven axisymmetric body with a plane of symmetry. A flat plate strut was attached to the upper surface of the axisymmetric body, giving a configuration like that of a SWATH-type ship, with the free surface replaced by the plane of symmetry. All mean flow and turbulent flow parameters were measured at three streamwise stations. The measurements were performed for the self-propelled condition and 100 percent over-thrust condition. In the far wake, the center of the wake was found to migrate towards the plane of symmetry. Some interactions were noted between the wakes of the propeller-driven axisymmetric body and that of the flat plate strut—yielding lower axial velocities, higher turbulence intensities and larger static pressure changes compared to regions free of such interference. Comparisons of these effects in the self-propelled case, 100 percent over-thrust case and a previous unpropelled case are given. Spectral measurements were also performed in both near-wake and far-wake regions.
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Kraft, Wayne N., and Malcolm J. Andrews. "Experimental Investigation of Unstably Stratified Buoyant Wakes." Journal of Fluids Engineering 128, no. 3 (November 1, 2005): 488–93. http://dx.doi.org/10.1115/1.2174060.

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A water channel has been used as a statistically steady experiment to investigate the development of a buoyant plane wake. Parallel streams of hot and cold water are initially separated by a splitter plate and are oriented to create an unstable stratification. At the end of the splitter plate, the two streams are allowed to mix and a buoyancy-driven mixing layer develops. The continuous, unstable stratification inside the developing mixing layer provides the necessary environment to study the buoyant wake. Downstream a cylinder was placed at the center of the mixing layer. As a result the dynamic flows of the plane wake and buoyancy-driven mixing layer interact. Particle image velocimetry and a high-resolution thermocouple system have been used to measure the response of the plane wake to buoyancy driven turbulence. Velocity and density measurements are used as a basis from which we describe the transition, and return to equilibrium, of the buoyancy-driven mixing layer. Visual observation of the wake does not show the usual vortex street associated with a cylinder wake, but the effect of the wake is apparent in the measured vertical velocity fluctuations. An expected peak in velocity fluctuations in the wake is found, however the decay of vertical velocity fluctuations occurs at a reduced rate due to vertical momentum transport into the wake region from buoyancy-driven turbulence. Therefore for wakes where buoyancy is driving the motion, a remarkably fast recovery of a buoyancy-driven Rayleigh-Taylor mixing in the wake region is found.
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Key, Nicole L. "Influence of Upstream and Downstream Compressor Stators on Rotor Exit Flow Field." International Journal of Rotating Machinery 2014 (2014): 1–10. http://dx.doi.org/10.1155/2014/392352.

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Measurements acquired at the rotor exit plane illuminate the interaction of the rotor with the upstream vane row and the downstream vane row. The relative phase of the upstream and downstream vane rows is adjusted using vane clocking so that the effect of the upstream propagating potential field from the downstream stator can be distinguished from the effects associated with the wakes shed from the upstream stator. Unsteady absolute flow angle information shows that the downstream potential field causes the absolute flow angle to increase in the vicinity of the downstream stator leading edge. The presence of Stator 1 wake is also detected at this measurement plane using unsteady total pressure data. The rotor wakes are measured at different circumferential locations across the vane passage, and the influence of Stator 1 wake on the suction side of the rotor wake is evident. Also, the influence of the downstream stator is detected on the pressure side of the rotor wake for a particular clocking configuration. Understanding the role of the surrounding vane rows on rotor wake development will lead to improved comparison between experimental data and results from computational models.
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Zhou, Y., and R. A. Antonia. "Critical points in a turbulent near wake." Journal of Fluid Mechanics 275 (September 25, 1994): 59–81. http://dx.doi.org/10.1017/s0022112094002284.

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Velocity data were obtained in the turbulent wake of a circular cylinder with an orthogonal array of sixteen X-wires, eight in the (x, y)-plane and eight in the (x, z)-plane. By applying the phase-plane technique to these data, three types of critical points (where the velocity is zero and the streamline slope is indeterminate) were identified. Of these, foci and saddle points occurred most frequently, although a significant number of nodes was also found. Flow topology and properties associated with these points were obtained in each plane. Saddle-point regions associated with spanwise vortices provide the dominant contribution to the Reynolds shear stress and larger contributions to the normal stresses than focal regions. The topology was found to be in close agreement with that obtained from other methods of detecting features of the organized motion. The inter-relationship between critical points simultaneously identified in the two planes can provide some insight into the three-dimensionality of the organized motion. Foci in the (x, z)-plane correspond, with relatively high probability and almost negligible streamwise separation, to saddle points in the (x, y)-plane and are interpreted in terms of ribs aligned with the diverging separatrix between consecutive spanwise vortex rolls. Foci in the (x, z)-plane which correspond, with relatively weak probability, to foci in the (x, y)-plane seem consistent with a distortion of the vortex rolls in the (y, z)-plane.
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El Khoury, George K., Helge I. Andersson, and Bjørnar Pettersen. "Wakes behind a prolate spheroid in crossflow." Journal of Fluid Mechanics 701 (May 18, 2012): 98–136. http://dx.doi.org/10.1017/jfm.2012.135.

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AbstractViscous laminar flow past a prolate $(L/ d= 6)$ spheroid has been investigated numerically at seven different Reynolds numbers; $\mathit{Re}= 50, 75, 100, 150, 200, 250$ and $300$. In contrast to all earlier investigations, the major axis of the spheroid was oriented perpendicular to the free stream flow. As expected, the flow field in the wake showed a strong resemblance of that observed behind a finite-length circular cylinder, yet had features observed in the axisymmetric wake behind a sphere. The following different flow regimes were observed in the present computational study: (i) steady laminar flow with massive flow separation and symmetry about the equatorial and the meridional planes at $\mathit{Re}= 50$; (ii) steady laminar flow with massive flow separation and symmetry about the equatorial and the meridional plane at $\mathit{Re}= 75$, but the flow in the equatorial plane did no longer resemble the steady wake behind a circular cylinder; (iii) unsteady laminar flow with Strouhal number $0. 109$ and symmetry about the equatorial plane at $\mathit{Re}= 100$; (iv) unsteady laminar flow with two distinct frequencies and without any planar symmetries at $\mathit{Re}= 200$; (v) transitional flow with a dominant shedding frequency $\mathit{St}= 0. 151$ and without any spatial symmetries at $\mathit{Re}= 300$. For all but the two lowest $\mathit{Re}$ hairpin vortices were alternately shed from the two sides of the spheroid and resulted in a ladder-like pattern of oppositely oriented vortex structures, in contrast with the single-sided shedding in the wake of a sphere. The contour of the very-near-wake mimicked the shape of the prolate spheroid. However, $15d$ downstream the major axis of the wake became aligned with the minor axis of the spheroid. This implies that an axis switching occurred some $10d$ downstream, i.e. the cross-section of the wake evolved such that the major and minor axes interchanged at a certain downstream location. This peculiar phenomenon has frequently been reported to arise for elliptical and rectangular jets, whereas observations of axis switching for asymmetric wakes are scarce.
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Dissertations / Theses on the topic "Plane Wake"

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Janajreh, Isam M. "Quantification of linear and nonlinear energy transfer processes in a plane wake." Thesis, Virginia Tech, 1994. http://hdl.handle.net/10919/41943.

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The transition to turbulence of plane wakes is characterized by the development of the velocity-fluctuation field from a spectrum of weak random background noise in the initial laminar wake to a nearly featureless broad spectrum of intense fluctuations within the turbulent wake. This transition has also been described as a sequence of instabilities and wave-wave interactions. In the initial small-amplitude stage,. a narrow, but continuous, band of dominant instability modes centered near the most unstable mode, known also as the fundamental mode, grow exponentially at rates that can be calculated from the linearized Navier-Stokes equations. As these modes grow, the nonlinear terms become more important and cannot be neglected anymore. The effect of these terms is to introduce wave-wave interactions that lead to quadratic energy transfer between the different spectral components of the velocity-fluctuation field. While the consequences of these interactions, such as broadening of the power spectra, have been observed in many experiments, the characteristics of these interactions have only been examined in limited cases. Previous measurements of the auto-bispectrum showed that three-wave interaction processes are important in the transitioning wake. However, quantification of these processes can only be obtained from measurement of the nonlinear energy transfer rates resulting from the nonlinear wave-wave interactions. Such quantification is very important for understanding the effects of the different mechanisms involved in the transition and final breakdown to turbulence. An understanding of these mechanisms and their effects can then be used to control the transition by enhancing certain mechanisms and reducing the role of others through external excitation. In this work, quantitative estimates of the auto-bispectrum, linear and quadratic coupling coefficients and the resulting energy transfer rates between the interacting waves at different locations are presented in controlled and natural transitions of the plane wake. The results show that, in both natural and controlled transitions, the underlying nonlinear dynamics are similar. Basically, nonlinear interactions between the instability modes result in energy transfer to harmonic bands as well as low-frequency difference components. These components play an important role in the transfer of energy to the sidebands and the valleys between the peaks. The results also show that, while energy-transfer rates in natural transition are lower than in controlled transition, the random nature of wave excitation in natural transition causes energy transfer to a band of low-frequency components which leads to energy transfer to many sidebands and results in a spectrum that differs dramatically from the one obtained in the controlled case where two instabilities are excited.
Master of Science

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Riba, Chad Alan. "Circulation control for download wake reduction on a scaled V-22 model." Morgantown, W. Va. : [West Virginia University Libraries], 2003. http://etd.wvu.edu/templates/showETD.cfm?recnum=2902.

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Thesis (M.S.)--West Virginia University, 2003.
Title from document title page. Document formatted into pages; contains x, 87 p. : ill. (some col.). Includes abstract. Includes bibliographical references (p. 72-73).
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O'Hara, Brian. "Comparison of numerical simulation to existing experimental data involving downwash wake reduction for the V-22 Osprey." Morgantown, W. Va. : [West Virginia University Libraries], 2005. https://eidr.wvu.edu/etd/documentdata.eTD?documentid=4355.

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Thesis (M.S.)--West Virginia University, 2005.
Title from document title page. Document formatted into pages; contains viii, 53 p. : ill. (some col.). Includes abstract. Includes bibliographical references (p. 45-46).
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Gibbs, Jason. "Experimental Determination of Lift and Lift Distributions for Wings In Formation Flight." Thesis, Virginia Tech, 2005. http://hdl.handle.net/10919/31301.

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Experimental methods for the investigation of trailing vortex strengths, total lift, and lift distributions for three-dimensional wings in close proximity flight were developed. With these experiments we model compound aircraft flight either docked tip-to-tip, or flying in formation. There is a distinct lack of experimental formation flight data using three-dimensional wing models for tests. The absence of fixed walls on either end of the wing permits the development of the asymmetric shedding of vortices, and the determination of the asymmetric circulation distribution induced by the proximity of the leading wing. The pair consisted of a swept NACA-0012 non-cambered wing simulating one half of a leading aircraft and a rectangular cambered NACA 63-420 wing simulating the trailing aircraft. Important aspects of the work included theoretical development, experimental setup, data acquisition and processing, and results validation. Experimentally determining the lift for formation flight, in addition to the local flow behavior for a pair of wings, can provide valuable insight for the proposition of flying actual aircraft in formation to increase mission efficiency. To eliminate the need for bulky mounting stings and direct load measurement devices that can potentially interfere with the local flowfield, a minimally invasive velocity probe method is developed. A series of experiments were performed to assist with the development of the method. Velocity and vorticity distributions obtained along a near-field plane were processed to calculate wingtip vortex strengths. Additionally, vortex position instabilities and the shedding of vorticity inboard of the wingtips were observed. To determine the circulation distributions for the trailing wing, the initial method is modified. By processing velocity information acquired in a near-field plane, both the lift and induced drag were calculated for the trailing airfoil. Comparisons are made to directly measured loads and to results reported earlier. Directly measured lift and drag coefficients were found to agree with existing literature.
Master of Science
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Kisiel, Thomas K. "Study of plane wave impingement on a thin plate capable of deformation." Thesis, Monterey, California. Naval Postgraduate School, 1991. http://hdl.handle.net/10945/26798.

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Subaschandar, N. "Turbulent Near Wake Behind An Infinitely Yawed Flat Plate." Thesis, Indian Institute of Science, 1995. http://hdl.handle.net/2005/146.

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Near wake is the region of wake flow just behind the trailing edge of the body where the flow is strongly influenced by the upstream flow conditions and also perhaps by the charac­teristics of the body. The present work is concerned with the study of the development of turbulent near wake behind an infinitely yawed flat plate. The turbulent near wake behind an infinitely yawed flat plate is the simplest of the three-dimensional turbulent near wake flows. The present study aims at providing a set of data on the turbulent near wake behind an infinitely yawed flat plate and also at understanding the development and structure of the near wake. Detailed measurements of mean and turbulent quantities have been made using 3-hole probe, X-wire and 3-wire hotwire probes. Further an asymptotic analysis of the two-dimensional turbulent near wake flow has been formulated for the near wake behind an infinitely yawed flat plate. The feature that the near wake which is dominated by mixing of the oncoming turbulent boundary layer retains, to a large extent, the memory of the turbulent structure of the boundary layer, has been exploited to develop this analysis. The analysis leads to three regions of the wake flow (the inner near wake, the outer near wake and the far wake) for which the governing equations are derived. The matching conditions among these regions lead to logarithmic variations in both normal and longitudinal directions in the overlapping regions surrounding the inner wake. These features are validated by the present results. A computational study involving seven well known turbulence models was also under­taken in order to assess the performance of the existing turbulence models in the prediction of the turbulent near wake behind an infinitely yawed flat plate. In this study all the seven models are implemented into a common flow solver code, thus eliminating the influence of grid size, initial conditions and different numerical schemes while making the comparison. This study shows that the K - e model performs better than other models in predicting the near wake behind an infinitely yawed flat plate.
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Le-Witt, Julian Alexander. "Asmptotically plane wave spacetimes." Thesis, Durham University, 2009. http://etheses.dur.ac.uk/251/.

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In this thesis we study aspects of plane wave spacetimes in the hope of shedding light of the nature of holography for plane waves. In particular, we would like to understand better the space of asymptotically plane wave solutions. We first review the necessary background on plane waves, variational principles for gravity and black holes in higher dimensions. We then propose a definition of asymptotically plane wave spacetimes in vacuum gravity in terms of the asymptotic fall-off of the metric and discuss the relation to previously constructed exact solutions. We construct a well-behaved action principle for such spacetimes, using the formalism developed by Mann and Marolf. We show that the action is finite on-shell and that the variational principle is well-defined for solutions of vacuum gravity satisfying our asymptotically plane wave fall-off conditions. Next we investigate the construction of black holes and black strings in vacuum plane wave spacetimes using the method of matched asymptotic expansions. We find solutions of the linearised equations of motion in the asymptotic region for a general source on a plane wave background. We observe that these solutions have some unusual propeties and do not satisfy our previously defined conditions for being asymptotically plane wave. Hence, the space of asymptotically plane solutions is restricted. We consider the solution in the near horizon region, treating the plane wave as a perturbation of a black object, and find that there is a regular black string solution. We find that no regular black hole solution exists, which is a counter-example to the conjecture of Emparan et. al. We end with a discussion of our results and suggest possible directions for future work.
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Pankiewicz, Ari. "Strings in plane wave backgrounds." Doctoral thesis, [S.l.] : [s.n.], 2003. http://deposit.ddb.de/cgi-bin/dokserv?idn=968799981.

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Pena, Moises. "Geodesics on Generalized Plane Wave Manifolds." CSUSB ScholarWorks, 2019. https://scholarworks.lib.csusb.edu/etd/866.

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A manifold is a Hausdorff topological space that is locally Euclidean. We will define the difference between a Riemannian manifold and a pseudo-Riemannian manifold. We will explore how geodesics behave on pseudo-Riemannian manifolds and what it means for manifolds to be geodesically complete. The Hopf-Rinow theorem states that,“Riemannian manifolds are geodesically complete if and only if it is complete as a metric space,” [Lee97] however, in pseudo-Riemannian geometry, there is no analogous theorem since in general a pseudo-Riemannian metric does not induce a metric space structure on the manifold. Our main focus will be on a family of manifolds referred to as a generalized plane wave manifolds. We will prove that all generalized plane wave manifolds are geodesically complete.
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10

Myung, Noh Hoon. "A high frequency analysis of electromagnetic plane wave scattering by perfectly-conducting semi-infinite parallel plate and rectangular waveguides with absorber coated inner walls /." The Ohio State University, 1986. http://rave.ohiolink.edu/etdc/view?acc_num=osu1487267546980859.

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Books on the topic "Plane Wake"

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Papageorgiou, Demetrious T. Linear instability of supersonic plane wakes. Hampton, Va: ICASE, 1989.

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Burmaster, Charles Lyman. Reciprocity calibration in a plane wave resonator. Monterey, Calif: Naval Postgraduate School, 1985.

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IEEE Antennas and Propagation Society., ed. The plane wave spectrum representation of electromagnetic fields. New York: Institute of Electrical and Electronics Engineers, 1996.

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Who will feed China?: Wake-up call for a small planet. London: Earthscan, 1995.

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Brown, Lester Russell. Who will feed China?: Wake-up call for a small planet. New York, N.Y: W.W. Norton, 1995.

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Who will feed China?: Wake-up call for a small planet. New York: W.W. Norton & Co., 1995.

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Moments out of place: Contemplations in haiku and tanka. Bloomington, IN, USA: AuthorHouse, 2015.

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The third wave of asbestos disease: Asbestos in place. Washington, D.C: Workplace Health Fund, 1990.

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9

Walenta, Z. A. Mach reflection of a moving, plane shock wave under rarefied flow conditions. Warsaw, Poland: Dept. of Fluid Mechanics, Institute of Fundamental Technological Research, Polish Academy of Sciences, 1986.

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Harvey, J. K. Dispersion in the wakes of aircraft: An investigation of the effects of a ground plane on trailing vortices. London: Imperial College of Science and Technology, 1986.

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Book chapters on the topic "Plane Wake"

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Davila, J. B., M. R. Hajj, R. W. Miksad, and E. J. Powers. "Wavenumber Mismatch of Interacting Modes in a Plane Wake." In Advances in Turbulence IV, 385–89. Dordrecht: Springer Netherlands, 1993. http://dx.doi.org/10.1007/978-94-011-1689-3_61.

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Antonia, R. A., L. W. B. Browne, and D. K. Bisset. "Topology of Organised Structures in a Turbulent Plane Wake." In Advances in Turbulence, 337–45. Berlin, Heidelberg: Springer Berlin Heidelberg, 1987. http://dx.doi.org/10.1007/978-3-642-83045-7_38.

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Grinstein, F. F., F. Hussain, and J. P. Boris. "Dynamics and Topology of Coherent Structures in a Plane Wake." In Advances in Turbulence 3, 34–41. Berlin, Heidelberg: Springer Berlin Heidelberg, 1991. http://dx.doi.org/10.1007/978-3-642-84399-0_4.

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Jeong, J., F. F. Grinstein, F. Hussain, and N. Albanis. "Eduction of Coherent Structures in a Numerically Simulated Plane Wake." In Eddy Structure Identification in Free Turbulent Shear Flows, 65–75. Dordrecht: Springer Netherlands, 1993. http://dx.doi.org/10.1007/978-94-011-2098-2_7.

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Sharma, S. D., and R. K. Sahoo. "Control of the Periodic Wake Behind a Plane Blunt Base." In IUTAM Symposium on Mechanics of Passive and Active Flow Control, 267–72. Dordrecht: Springer Netherlands, 1999. http://dx.doi.org/10.1007/978-94-011-4199-4_43.

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Ngouani, M. M. Siewe, Yong Kang Chen, R. Day, and O. David-West. "Low-Speed Aerodynamic Analysis Using Four Different Turbulent Models of Solver of a Wind Turbine Shroud." In Springer Proceedings in Energy, 149–54. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-63916-7_19.

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AbstractThis study presents the effect of four different turbulent models of solver on the aerodynamic analysis of a shroud at wind speed below 6 m/s. The converting shroud uses a combination of a cylindrical case and an inverted circular wing base which captures the wind from a 360° direction. The CFD models used are: the SST (Menter) k-ω model, the Reynolds Stress Transport (RST) model, the Improved Delay Detached Eddies Simulation model (IDDES) SST k-ω model and the Large Eddies Simulation Wall Adaptive model. It was found that all models have predicted a convergent surface pressure. The RST, the IDDES and the WALE LES are the only models which have well described regions of pressure gradient. They have all predicted a pressure difference between the planes (1–5) which shows a movement of the air from the lower plane 1 (inlet) to the higher plane 5 (outlet). The RST and IDDES have predicted better vorticities on the plane 1 (inlet). It was also found that the model RST, IDDES, and WALE LES have captured properly the area of turbulences across the internal region of the case. All models have predicted the point of flow separation. They have also revealed that the IDDES and the WALE LES can capture and model the wake eddies at different planes. Thus, they are the most appropriate for such simulation although demanding in computational power. The movement of air predicted by almost all models could be used to drive a turbine.
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Heitz, D., G. Arroyo, P. Marchal, J. Delville, J. H. Garem, and J. P. Bonnet. "Turbulent Plane Mixing Layer Perturbed by the Wake of a Circular Cylinder." In Fluid Mechanics and Its Applications, 309–12. Dordrecht: Springer Netherlands, 1998. http://dx.doi.org/10.1007/978-94-011-5118-4_76.

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Miksad, R. W., M. R. Hajj, R. S. Solis, and E. J. Powers. "The Effect of Mean Flow Unstediness on the Dynamics of a Plane Wake." In Bluff-Body Wakes, Dynamics and Instabilities, 131–34. Berlin, Heidelberg: Springer Berlin Heidelberg, 1993. http://dx.doi.org/10.1007/978-3-662-00414-2_31.

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Aronson, D., and L. Löfdahl. "An Estimate of the Pressure-Strain Rate Tensor in a Plane Cylinder Wake." In Fluid Mechanics and Its Applications, 6–10. Dordrecht: Springer Netherlands, 1995. http://dx.doi.org/10.1007/978-94-011-0457-9_2.

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Geropp, D., and A. Leder. "The Flow Structure in the Wake and Separated Region of Plane and Axisymmetric Bodies." In Notes on Numerical Fluid Mechanics (NNFM), 142–49. Wiesbaden: Vieweg+Teubner Verlag, 1993. http://dx.doi.org/10.1007/978-3-663-13986-7_20.

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Conference papers on the topic "Plane Wake"

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Kraft, Wayne N., and Malcolm J. Andrews. "Experimental Investigation of Stratified, Buoyant Wakes." In ASME 2004 Heat Transfer/Fluids Engineering Summer Conference. ASMEDC, 2004. http://dx.doi.org/10.1115/ht-fed2004-56623.

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The development of a buoyant plane wake has been investigated experimentally. A water channel has been used as a statistically steady experiment to investigate the plane wakes. Parallel streams of hot and cold water are initially separated by a splitter plate. The streams are oriented such that the cold fluid is above the hot fluid, resulting in an unstable stratification. At the end of the splitter plate, the two streams are allowed to mix and a buoyancy driven mixing layer develops. Downstream of the splitter plate, growth of the turbulent buoyancy-driven mix is disrupted by a cylinder. The cylinder is located at the centerline of the mixing layer and associated wake. As a result the dynamic flows of the plane wake and buoyancy driven mixing layer interact. Particle image velocimetry (PIV), and a high-resolution thermocouple system are used to measure the response of the plane wake to buoyancy driven turbulence. Velocity and density measurements are used as a basis from which we describe the transition, and return to equilibrium, of the buoyancy driven mixing layer. We found for wakes where buoyancy is driving the motion, a remarkably fast recovery of a Rayleigh-Taylor mix in the wake region.
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Dadmarzi, Fatemeh Hoseini, Vagesh D. Narasimhamurthy, Helge I. Andersson, and Bjørnar Pettersen. "The Wake Behind Two Intersecting Flat Plates." 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/fedsm2014-21208.

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The wake flow behind two intersecting flat plates forming a cross is studied by means of direct numerical simulation (DNS) at low Reynolds number. The Reynolds number based on the plate width, d, and the inflow velocity, U0, is 100. The flat plate structure is in one plane. Away from the intersecting center part, vortex streets can be observed similar to the wake flow behind a single normal flat plate. On the other hand, the flow is completely three-dimensional in the vicinity of the intersecting region where the wakes from each of the two normal flat plates interact with each other. The mean pressure distribution on the structure is evaluated in order to study the total drag force as well as the local force distribution.
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Cain, Alan, Michael Rogers, and Valdis Kibens. "Simulations of high-frequency excitation of a plane wake." In 39th Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2001. http://dx.doi.org/10.2514/6.2001-514.

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McFarland, Vernon E., and William G. Tiederman. "Viscous Interaction Upstream and Downstream of a Turbine Stator Cascade With a Periodic Wake Field." In ASME 1992 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1992. http://dx.doi.org/10.1115/92-gt-162.

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The influence of periodic rotor wakes has a substantial effect on the flow in a turbine stator cascade. A mechanism located upstream of a linear, low-aspect ratio, turbine cascade simulated wakes shed from rotor blades by translating cylindrical rods across the inlet of the cascade. In order to provide a test case to increase our fundamental understanding of the unsteady viscous flow typical of a gas turbine engine, three components of velocity, phase-locked into sixteen time windows which encompassed the rotor period, were measured at two upstream planes and one downstream plane. Due to the effects in the endwall region, the wake in the inlet plane bows in the tangential direction as the wake translates into the passage. The effects of the passage vortex do not decay significantly within one chord downstream of the exit of the cascade. The location of the passage vortex at the far downstream exit plane is dependent upon rotor position, as reported in earlier studies. A complete data set of the mean and fluctuating velocity components at all sixteen time windows is available on diskette.
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Wu, J., B. Ondrusek, and J. Wu. "Exact force diagnostics of vehicles based on wake-plane data." In 34th Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1996. http://dx.doi.org/10.2514/6.1996-559.

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Arnold, Matthias, Po Wen Cheng, Philipp Daus, and Frank Biskup. "Tidal Current Turbine Wake and Park Layout in Transient Environments." In ASME 2014 33rd International Conference on Ocean, Offshore and Arctic Engineering. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/omae2014-24067.

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Due to orbital velocities of the waves, the characteristics of tidal current turbines change over time. Therefore the induction factor and subsequent the wake is time dependent. Within the present research this time dependency is investigated by using Computational Fluid Dynamics (CFD) with Virtual Free Surface (VFS) and Actuator Disc (ACD) models. Based on this setup several different wave and current scenarios are simulated and analyzed with respect to the transient velocities in the turbine wake. Special respect is taken to the velocity undulations radiated by the changing apparent velocities in the rotor plane. These undulations move with the wake of the tidal current turbines and increase the wave loads on 2nd row turbines in a park. This paper presents an efficient method for simulation of wave and park interactions and investigates dynamic turbine wakes under a large variety of parameters. Based on these simulations a suggestion for a tidal park design with respect to a balance of fatigue loads and power output is concluded.
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Lav, Chitrarth, Jimmy Philip, and Richard Sandberg. "Video: Effect of pressure gradients on a confined turbulent plane wake." In 72th Annual Meeting of the APS Division of Fluid Dynamics. American Physical Society, 2019. http://dx.doi.org/10.1103/aps.dfd.2019.gfm.v0088.

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BOGUCZ, E. "The symmetric turbulent plane wake downstream of a sharp trailing edge." In 29th Aerospace Sciences Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1991. http://dx.doi.org/10.2514/6.1991-612.

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Hardin, Jay, Frank Wang, and Hadi Wassaf. "Sound Generation by Aircraft Wake Vortices Interacting with the Ground Plane." In 10th AIAA/CEAS Aeroacoustics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2004. http://dx.doi.org/10.2514/6.2004-2881.

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Braud, Caroline, Dominique Heitz, Georges Arroyo, Joel Delville, and Jean-Paul Bonnet. "LOW-DIMENSIONAL GALERKIN MODEL OF A PLANE MIXING LAYER-WAKE INTERACTION." In Third Symposium on Turbulence and Shear Flow Phenomena. Connecticut: Begellhouse, 2003. http://dx.doi.org/10.1615/tsfp3.1410.

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Reports on the topic "Plane Wake"

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Chen, J., B. Cantwell, and N. Mansour. Direct numerical simulations of a plane compressible wake: Stability, vorticity dynamics, and topology. Office of Scientific and Technical Information (OSTI), November 1989. http://dx.doi.org/10.2172/6912304.

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Symes, William W. The Plane-Wave Detection Problem. Fort Belvoir, VA: Defense Technical Information Center, April 1993. http://dx.doi.org/10.21236/ada455475.

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Fritz, J. N. A simple plane-wave explosive lens. Office of Scientific and Technical Information (OSTI), December 1990. http://dx.doi.org/10.2172/6430373.

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Sadri, D. The Plane-Wave/Super Yang-Mills Duality. Office of Scientific and Technical Information (OSTI), October 2003. http://dx.doi.org/10.2172/826467.

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Leung, K. M., and Y. F. Liu. Photon Band Structures: The Plane-Wave Method. Fort Belvoir, VA: Defense Technical Information Center, May 1990. http://dx.doi.org/10.21236/ada222662.

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Mirth, Lee. Focal Plane Array-Based Millimeter Wave Imaging Radiometer. Fort Belvoir, VA: Defense Technical Information Center, June 2003. http://dx.doi.org/10.21236/ada417452.

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Butler, M. A., S. J. Martin, J. J. Spates, and M. A. Mitchell. Magnetically-excited flexural plate wave device. Office of Scientific and Technical Information (OSTI), May 1997. http://dx.doi.org/10.2172/474933.

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Herrmann, R. B., T. A. Mokhtar, T. M. Chang, C. J. Ammon, and H. A. Ghalib. Wave Propagation in the Arabian Plate. Fort Belvoir, VA: Defense Technical Information Center, June 1998. http://dx.doi.org/10.21236/ada382019.

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Symes, William W. Plane-Wave Detection: a Nonlinearly Ill-Posed Inverse Problem. Fort Belvoir, VA: Defense Technical Information Center, September 1989. http://dx.doi.org/10.21236/ada452709.

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Bowman, Daniel. Energy flux of a continuous acoustic plane wave train. Office of Scientific and Technical Information (OSTI), December 2017. http://dx.doi.org/10.2172/1415114.

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