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Articles de revues sur le sujet « Wake-Induced Transition »

Auteur : Grafiati

Publié le 10 mars 2023

Mis à jour le 31 juillet 2025

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1

Mandal, A. C., and J. Dey. "An experimental study of boundary layer transition induced by a cylinder wake." Journal of Fluid Mechanics 684 (September 1, 2011): 60–84. http://dx.doi.org/10.1017/jfm.2011.270.

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AbstractBoundary layer transition induced by the wake of a circular cylinder in the free stream has been investigated using the particle image velocimetry technique. Some differences between simulation and experimental studies have been reported in the literature, and these have motivated the present study. The appearance of spanwise vortices in the early stage is further confirmed here. A spanwise vortex appears to evolve into a $ \mrm{\Lambda} $/hairpin vortex; the flow statistics also confirm such vortices. With increasing Reynolds number, based on the cylinder diameter, and with decreasing

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2

Kyriakides, N. K., E. G. Kastrinakis, S. G. Nychas, and A. Goulas. "Boundary Layer Transition Induced by a Von Karman Vortex Street Wake." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 210, no. 2 (1996): 167–79. http://dx.doi.org/10.1243/pime_proc_1996_210_358_02.

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A study has been made of the process of laminar to turbulent transition induced by a von Karman vortex street wake, in the boundary layer on a flat plate. The boundary layer developed under zero pressure gradient conditions while the vortex street was generated by a cylinder positioned in the free stream. Hot-wire measurements over a range of Strouhal frequencies and free stream velocities were used for the identification of the transition onset. From the analysis of the experimental data, two different transition mechanisms known in the literature as ‘strong’ wake and ‘weak’ wake induced tran

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3

Mayle, R. E., and K. Dullenkopf. "A Theory for Wake-Induced Transition." Journal of Turbomachinery 112, no. 2 (1990): 188–95. http://dx.doi.org/10.1115/1.2927632.

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A theory for transition from laminar to turbulent flow as the result of unsteady, periodic passing of turbulent wakes in the free stream is developed using Emmons’ transition model. Comparisons made to flat plate boundary layer measurements and airfoil heat transfer measurements confirm the theory.

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4

Kyriakides, N. K., E. G. Kastrinakis, S. G. Nychas, and A. Goulas. "A bypass wake induced laminar/turbulent transition." European Journal of Mechanics - B/Fluids 18, no. 6 (1999): 1049–65. http://dx.doi.org/10.1016/s0997-7546(99)00140-5.

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Funazaki, K. "Unsteady Boundary Layers on a Flat Plate Disturbed by Periodic Wakes: Part I—Measurement of Wake-Affected Heat Transfer and Wake-Induced Transition Model." Journal of Turbomachinery 118, no. 2 (1996): 327–36. http://dx.doi.org/10.1115/1.2836643.

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Measurements of wake-affected heat transfer distributions on a flat plate are made by use of a wake generator that consists of a rotating disk and several types of circular cylinder. The main purpose of this study is to construct a wake-induced transition model in terms of an intermittency factor, considering the evolution of the wake-induced turbulent region, a so-called turbulent patch in a distance–time diagram. A comparison between the proposed transition model and the measured heat transfer data reveals that the transition model yields good agreement with the measured data of all test con

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6

Funazaki, K. "Unsteady Boundary Layers on a Flat Plate Disturbed by Periodic Wakes: Part II—Measurements of Unsteady Boundary Layers and Discussion." Journal of Turbomachinery 118, no. 2 (1996): 337–44. http://dx.doi.org/10.1115/1.2836644.

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As the second part of the study, detailed hot-wire anemometry measurements of wake-affected boundary layers on the flat plate are made. These measurements are organized in order, first, to check the standpoint of the modeling of the wake-induced transition proposed in Part I, and second, to observe wake–boundary layer interaction in detail from a viewpoint of direct and indirect effect of the wake passage upon turbulent spot generation within the boundary layer, as described by Walker (1993). The validity of the presumed state of the wake-affected boundary layer in the distance–time domain, wh

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7

Wang, Haiyang, Zaijie Liu, Hexia Huang, Huijun Tan, and Dan Zhao. "Direct Numerical Simulation of Boundary Layer Transition Induced by Roughness Elements in Supersonic Flow." Aerospace 12, no. 3 (2025): 242. https://doi.org/10.3390/aerospace12030242.

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Current research on the transition mechanisms induced by moderate-height roughness elements remains insufficiently explored. Hence, direct numerical simulation (DNS) and BiGlobal stability analysis are employed in this study to investigate boundary layer transition from laminar to turbulent flow induced by moderate-height isolated roughness elements and roughness strips under a supersonic freestream at Mach 3.5. Analysis of DNS results reveals that the isolated roughness element induces transition within the boundary layer, characterized by two high-speed streaks in the wake. This transition i

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8

Wright, L., and M. T. Schobeiri. "The Effect of Periodic Unsteady Flow on Aerodynamics and Heat Transfer on a Curved Surface." Journal of Heat Transfer 121, no. 1 (1999): 22–33. http://dx.doi.org/10.1115/1.2825954.

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Aerodynamic and heat transfer investigations were performed on a constant curvature curved plate in a subsonic wind tunnel facility for various wake passing frequencies under zero pressure gradient conditions. Steady and unsteady boundary layer transition measurements were taken on the concave surface at different wake passing frequencies in which a rotating squirrel cage was used to generate the unsteady wake flow. The data were analyzed using time-averaged and ensemble averaged techniques to provide insight into the growth of the boundary layer and transition. Ensemble averaged turbulence in

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9

Schulte, V., and H. P. Hodson. "Unsteady Wake-Induced Boundary Layer Transition in High Lift LP Turbines." Journal of Turbomachinery 120, no. 1 (1998): 28–35. http://dx.doi.org/10.1115/1.2841384.

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The development of the unsteady suction side boundary layer of a highly loaded LP turbine blade has been investigated in a rectilinear cascade experiment. Upstream rotor wakes were simulated with a moving-bar wake generator. A variety of cases with different wake-passing frequencies, different wake strength, and different Reynolds numbers were tested. Boundary layer surveys have been obtained with a single hotwire probe. Wall shear stress has been investigated with surface-mounted hot-film gages. Losses have been measured. The suction surface boundary layer development of a modern highly loade

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10

Schobeiri, M. T., L. Wright, and P. Chakka. "Periodic Unsteady Flow Aerodynamics and Heat Transfer: Studies on a Curved Surface, Combined Part I and II." International Journal of Rotating Machinery 6, no. 6 (2000): 393–416. http://dx.doi.org/10.1155/s1023621x00000373.

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Aerodynamic and heat transfer investigations were done on a constant curvature curved plate in a subsonic wind tunnel facility for various wake passing frequencies and zero pressure gradient conditions. Steady and unsteady boundary layer transition measurements were taken on the concave surface of the curved plate at different wake passing frequencies where a rotating squirrel-cage generated the unsteady wake flow. The data were analyzed using timeaveraged and ensemble-averaged techniques to provide insight into the growth of the boundary layer and transition. Ensemble-averaged turbulence inte

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11

PAN, CHONG, JIN JUN WANG, PAN FENG ZHANG, and LI HAO FENG. "Coherent structures in bypass transition induced by a cylinder wake." Journal of Fluid Mechanics 603 (April 30, 2008): 367–89. http://dx.doi.org/10.1017/s0022112008001018.

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Flat-plate boundary layer transition induced by the wake vortex of a two-dimensional circular cylinder is experimentally investigated. Combined visualization and velocity measurements show a different transition route from the Klebanoff mode in free-stream turbulence-induced transition. This transition scenario is mainly characterized as: (i) generation of secondary transverse vortical structures near the flat plate surface in response to the von Kármán vortex street of the cylinder; (ii) formation of hairpin vortices due to the secondary instability of secondary vortical structures; (iii) gro

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12

Mayle, R. E., and K. Dullenkopf. "More on the Turbulent-Strip Theory for Wake-Induced Transition." Journal of Turbomachinery 113, no. 3 (1991): 428–32. http://dx.doi.org/10.1115/1.2927892.

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A theory for transition from laminar to turbulent flow with an unsteady, periodic passing of turbulent wakes in the free stream has recently been presented by the authors. The theory considers a time-averaged transitional flow caused by the formation and propagation of turbulent strips along the surface. To apply the theory, however, both the origin and a quantity related to the production rate of these turbulent strips must be known. In this paper, after a brief review of the theory, a dimensional analysis of the problem is presented and data from experiments reexamined in light of the result

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13

Kim, K., and M. E. Crawford. "Prediction of Transitional Heat Transfer Characteristics of Wake-Affected Boundary Layers." Journal of Turbomachinery 122, no. 1 (1999): 78–87. http://dx.doi.org/10.1115/1.555430.

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The presence of wake-passing in the gas turbine environment significantly modifies the heat transfer characteristics on the downstream blade surface by causing wake-induced transition. In this study, time-dependent boundary layer calculations were carried out using a model for wake-induced transition based on a prescribed time-dependent intermittent function. The model is determined from the well-known turbulent spot propagation theory in a time-space diagram and from experimental evidence in the ensemble-averaged sense. Time-averaged heat transfer distributions are evaluated and compared with

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14

Hodson, H. P., J. S. Addison, and C. A. Shepherson. "Models for unsteady wake-induced transition in axial turbomachines." Journal de Physique III 2, no. 4 (1992): 545–74. http://dx.doi.org/10.1051/jp3:1992147.

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15

Rahman, M. M., Baojun Li, K. Hasan, and Sheng Chen. "An algebraic transition model for fluid flows." Journal of Physics: Conference Series 2512, no. 1 (2023): 012004. http://dx.doi.org/10.1088/1742-6596/2512/1/012004.

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Abstract An algebraic (zero-equation) transition model is developed to capture multiple transition mechanisms. The newly devised algebraic transition model is parameterized using “flow-structure-adaptive” variables and coupled with the truncated Spalart-Allmaras (SA) turbulence model. The intermittency factor γ relies on “local flow information” and is directly linked to the “vorticity-based production” term of the SA model. Splitting γ into lower and higher regimes of the “free-stream turbulence intensity” enhances the model coefficient calibration and predictions of various phenomena (“natur

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16

Stieger, R. D., and H. P. Hodson. "The Transition Mechanism of Highly Loaded Low-Pressure Turbine Blades." Journal of Turbomachinery 126, no. 4 (2004): 536–43. http://dx.doi.org/10.1115/1.1773850.

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A detailed experimental investigation was conducted into the interaction of a convected wake and a separation bubble on the rear suction surface of a highly loaded low-pressure (LP) turbine blade. Boundary layer measurements, made with 2D LDA, revealed a new transition mechanism resulting from this interaction. Prior to the arrival of the wake, the boundary layer profiles in the separation region are inflexional. The perturbation of the separated shear layer caused by the convecting wake causes an inviscid Kelvin-Helmholtz rollup of the shear layer. This results in the breakdown of the laminar

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17

Walters, D. Keith, and James H. Leylek. "Computational Fluid Dynamics Study of Wake-Induced Transition on a Compressor-Like Flat Plate." Journal of Turbomachinery 127, no. 1 (2005): 52–63. http://dx.doi.org/10.1115/1.1791650.

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Recent experimental work has documented the importance of wake passing on the behavior of transitional boundary layers on the suction surface of axial compressor blades. This paper documents computational fluid dynamics (CFD) simulations using a commercially available general-purpose CFD solver, performed on a representative case with unsteady transitional behavior. The study implements an advanced version of a three-equation eddy-viscosity model previously developed and documented by the authors, which is capable of resolving boundary layer transition. It is applied to the test cases of stead

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18

Funazaki, K., and E. Koyabu. "Effects of Periodic Wake Passing Upon Flat-Plate Boundary Layers Experiencing Favorable and Adverse Pressure Gradients." Journal of Turbomachinery 121, no. 2 (1999): 333–40. http://dx.doi.org/10.1115/1.2841319.

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This paper deals with the investigation of wake-disturbed boundary layer on a flat-plate model with an elliptic leading edge. The wakes are generated by the transversely moving bars in front of the test model. The main focus of this paper is how the wake passage affects the transitional behavior of the boundary layer under the influence of favorable and adverse pressure gradients over the test surface. Detailed measurements of the boundary layer are conducted by the use of hot-wire anemometry. An ensemble-averaging technique is also employed in order to extract the periodic events associated w

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19

Kubacki, Slawomir, and Erik Dick. "An algebraic intermittency model for bypass, separation-induced and wake-induced transition." International Journal of Heat and Fluid Flow 62 (December 2016): 344–61. http://dx.doi.org/10.1016/j.ijheatfluidflow.2016.09.013.

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20

De Tullio, Nicola, and Neil D. Sandham. "Influence of boundary-layer disturbances on the instability of a roughness wake in a high-speed boundary layer." Journal of Fluid Mechanics 763 (December 11, 2014): 136–65. http://dx.doi.org/10.1017/jfm.2014.663.

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AbstractThe excitation of instability modes in the wake generated behind a discrete roughness element in a boundary layer at Mach 6 is analysed through numerical simulations of the compressible Navier–Stokes equations. Recent experimental observations show that transition to turbulence in high-speed boundary layers during re-entry flight is dominated by wall roughness effects. Therefore, understanding the roughness-induced transition to turbulence in this flow regime is of primary importance. Our results show that a discrete roughness element with a height of about half the local boundary-laye

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21

Stieger, R. D., and H. P. Hodson. "Unsteady dissipation measurements on a flat plate subject to wake passing." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 217, no. 4 (2003): 413–19. http://dx.doi.org/10.1243/095765003322315478.

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Boundary layer measurements were performed on a flat plate with an imposed pressure gradient typical of a high-lift low-pressure (LP) turbine blade and subject to incoming turbulent wakes shed from a moving bar wake generator. A multiple-orientation one-dimensional laser doppler anemometry (LDA) technique was used to measure the ensemble-average mean flow and Reynolds stresses. These ensembleaverage measurements were used to calculate the boundary layer dissipation, thereby providing unprecedented experimental evidence of the loss-reducing mechanisms associated with wake-induced transition. Th

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22

COULL, JOHN D., and HOWARD P. HODSON. "Unsteady boundary-layer transition in low-pressure turbines." Journal of Fluid Mechanics 681 (July 1, 2011): 370–410. http://dx.doi.org/10.1017/jfm.2011.204.

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This paper examines the transition process in a boundary layer similar to that present over the suction surfaces of aero-engine low-pressure (LP) turbine blades. This transition process is of significant practical interest since the behaviour of this boundary layer largely determines the overall efficiency of the LP turbine. Modern ‘high-lift’ blade designs typically feature a closed laminar separation bubble on the aft portion of the suction surface. The size of this bubble and hence the inefficiency it generates is controlled by the transition between laminar and turbulent flow in the bounda

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23

Wu, Xiaohua, and Paul A. Durbin. "Boundary Layer Transition Induced by Periodic Wakes." Journal of Turbomachinery 122, no. 3 (1998): 442–49. http://dx.doi.org/10.1115/1.1303076.

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Turbulent wakes swept across a flat plate boundary layer simulate the phenomenon of wake-induced bypass transition. Benchmark data from a direct numerical simulation of this process are presented and compared to Reynolds-averaged predictions. The data are phase-averaged skin friction and mean velocities. The predictions and data are found to agree in many important respects. One discrepancy is a failure to reproduce the skin friction overshoot following transition. [S0889-504X(00)00503-1]

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24

Wu, Xiaohua, and Kyle D. Squires. "Three-Dimensional Boundary Layers Over an Infinite Swept Bump and Free Wing." Journal of Fluids Engineering 117, no. 4 (1995): 605–11. http://dx.doi.org/10.1115/1.2817310.

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Three-dimensional laminar boundary layers past an infinite swept bump and free wing were investigated numerically using the fractional step method. The objective of the work was to study the effect of surface curvature induced changes in pressure gradient and changes in the freestream flow on boundary layer skewness and growth. Simulation results demonstrate that for flows over the bump the first transition from adverse to favorable pressure gradient occurs at the front concave/convex inflexion and the second transition from favorable to adverse pressure gradient occurs at the summit. For flow

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25

Walker, G. J., J. D. Hughes, and W. J. Solomon. "Periodic Transition on an Axial Compressor Stator: Incidence and Clocking Effects: Part I—Experimental Data." Journal of Turbomachinery 121, no. 3 (1999): 398–407. http://dx.doi.org/10.1115/1.2841332.

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Periodic wake-induced transition on the outlet stator of a 1.5-stage axial compressor is examined using hot-film arrays on both the suction and pressure surfaces. The time-mean surface pressure distribution is varied by changing the blade incidence, while the free-stream disturbance field is altered by clocking of the stator relative to an inlet guide vane row. Ensemble-averaged plots of turbulent intermittency and relaxation factor (extent of calmed flow following the passage of a turbulent spot) are presented. These show the strength of periodic wake-induced transition phenomena to be signif

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26

Funazaki, Ken-ichi, Takashi Kitazawa, and Takashi Watanabe. "Boundary Layer Transition Induced by Periodic Wake Passage. Effect of Velocity Fluctuation Caused by Wake Passage." Transactions of the Japan Society of Mechanical Engineers Series B 61, no. 583 (1995): 874–81. http://dx.doi.org/10.1299/kikaib.61.874.

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27

Halstead, D. E., D. C. Wisler, T. H. Okiishi, G. J. Walker, H. P. Hodson, and H. W. Shin. "Boundary Layer Development in Axial Compressors and Turbines: Part 1 of 4—Composite Picture." Journal of Turbomachinery 119, no. 1 (1997): 114–27. http://dx.doi.org/10.1115/1.2841000.

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Comprehensive experiments and computational analyses were conducted to understand boundary layer development on airfoil surfaces in multistage, axial-flow compressors and LP turbines. The tests were run over a broad range of Reynolds numbers and loading levels in large, low-speed research facilities which simulate the relevant aerodynamic features of modern engine components. Measurements of boundary layer characteristics were obtained by using arrays of densely packed, hot-film gauges mounted on airfoil surfaces and by making boundary layer surveys with hot wire probes. Computational predicti

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28

LO JACONO, DAVID, JUSTIN S. LEONTINI, MARK C. THOMPSON, and JOHN SHERIDAN. "Modification of three-dimensional transition in the wake of a rotationally oscillating cylinder." Journal of Fluid Mechanics 643 (December 24, 2009): 349–62. http://dx.doi.org/10.1017/s0022112009992370.

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A study of the flow past an oscillatory rotating cylinder has been conducted, where the frequency of oscillation has been matched to the natural frequency of the vortex street generated in the wake of a stationary cylinder, at Reynolds number 300. The focus is on the wake transition to three-dimensional flow and, in particular, the changes induced in this transition by the addition of the oscillatory rotation. Using Floquet stability analysis, it is found that the fine-scale three-dimensional mode that typically dominates the wake at a Reynolds number beyond that at the second transition to th

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29

Ye, Qingqing, Ferry F. J. Schrijer, and Fulvio Scarano. "Boundary layer transition mechanisms behind a micro-ramp." Journal of Fluid Mechanics 793 (March 14, 2016): 132–61. http://dx.doi.org/10.1017/jfm.2016.120.

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The early stage of three-dimensional laminar-to-turbulent transition behind a micro-ramp is studied in the incompressible regime using tomographic particle image velocimetry. Experiments are conducted at supercritical micro-ramp height $h$ based Reynolds number $Re_{h}=1170$. The measurement domain encompasses 6 ramp widths spanwise and 73 ramp heights streamwise. The mean flow topology reveals the underlying vortex structure of the wake flow with multiple pairs of streamwise counter-rotating vortices visualized by streamwise vorticity. The primary pair generates a vigorous upwash motion in th

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Solomon, W. J., and G. J. Walker. "Incidence Effects on Wake-Induced Transition on an Axial Compressor Blade." Journal of Propulsion and Power 16, no. 3 (2000): 397–405. http://dx.doi.org/10.2514/2.5603.

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Lardeau, S., and M. A. Leschziner. "Modeling of Wake-Induced Transition in Linear Low-Pressure Turbine Cascades." AIAA Journal 44, no. 8 (2006): 1854–65. http://dx.doi.org/10.2514/1.16470.

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OVCHINNIKOV, VICTOR, UGO PIOMELLI, and MEELAN M. CHOUDHARI. "Numerical simulations of boundary-layer transition induced by a cylinder wake." Journal of Fluid Mechanics 547, no. -1 (2006): 413. http://dx.doi.org/10.1017/s0022112005007342.

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33

Kubacki, S., K. Lodefier, R. Zarzycki, W. Elsner, and E. Dick. "Further Development of a Dynamic Intermittency Model For Wake-Induced Transition." Flow, Turbulence and Combustion 83, no. 4 (2009): 539–68. http://dx.doi.org/10.1007/s10494-009-9206-2.

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Pan, Chong, Jin-Jun Wang, and Guo-Sheng He. "Experimental Investigation of Wake-Induced Bypass Transition Control by Surface Roughness." Chinese Physics Letters 29, no. 10 (2012): 104704. http://dx.doi.org/10.1088/0256-307x/29/10/104704.

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Ouyang, Xiaoqing, Zhijun Lei, Hanliu Deng, et al. "Influence of Upstream Sweeping Wake Number on the Unsteady Flow Mechanism in an Integrated Aggressive Intermediate Turbine Duct." Machines 11, no. 7 (2023): 728. http://dx.doi.org/10.3390/machines11070728.

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This paper focuses on the dynamic internal flow in the integrated aggressive intermediate turbine duct (AITD) with different HPT wake numbers, using CFX Solver with dynamic Reynolds-averaged Navier–Stokes equations (RANS), the shear stress transmission κ-ω turbulence model (SST) and the γ-θ transition model. The HPT wakes are simulated using sweeping rods, with the number of rods ranging from 14 to 56 and a reduced frequency of 1.07. The increasing wake number reduces the radial pressure gradient in the integrated AITD, and then decelerates the radial migration and dissipation of wake vortices

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Messmer, Thomas, Joachim Peinke, and Michael Hölling. "Wind tunnel investigation on the recovery and dynamics of the wake of a floating offshore wind turbine subjected to low inflow turbulence." Journal of Physics: Conference Series 2767, no. 9 (2024): 092083. http://dx.doi.org/10.1088/1742-6596/2767/9/092083.

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Abstract Floating offshore wind turbines (FOWT) operate in various turbulent conditions, including low turbulence intensity situations (TI∞ ≤ 5%). In this paper, we investigate experimentally the wake of a model floating wind turbine subjected to inflow turbulence up to TI∞ ≈ 3%. We consider idealised surge platform motion and analyse wake measurements at different downstream positions x ∈ [4D, 8D]. The results show that rotor movements enhance wake recovery compared to the fixed wind turbine, especially for TI∞ ≤ 2%. The recovery of the moving wind turbine wake is progressively less affected

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37

Cho, N. H., X. Liu, W. Rodi, and B. Scho¨nung. "Calculation of Wake-Induced Unsteady Flow in a Turbine Cascade." Journal of Turbomachinery 115, no. 4 (1993): 675–86. http://dx.doi.org/10.1115/1.2929302.

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Numerical predictions are reported for two-dimensional unsteady flow in a linear turbine cascade, where the unsteadiness is caused by passing wakes generated by the preceding row of blades. In particular, an experiment is simulated in which the passing wakes were generated by cylinders moving on a rotating squirrel cage. Blade-to-blade calculations were carried out by solving the unsteady two dimensional flow equations with an accurate finite-volume procedure, thereby resolving the periodic unsteady motion. The effects of stochastic turbulent fluctuations are simulated with a two-layer turbule

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Loiseau, Jean-Christophe, Jean-Christophe Robinet, Stefania Cherubini, and Emmanuel Leriche. "Investigation of the roughness-induced transition: global stability analyses and direct numerical simulations." Journal of Fluid Mechanics 760 (November 4, 2014): 175–211. http://dx.doi.org/10.1017/jfm.2014.589.

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AbstractThe linear global instability and resulting transition to turbulence induced by an isolated cylindrical roughness element of height $h$ and diameter $d$ immersed within an incompressible boundary layer flow along a flat plate is investigated using the joint application of direct numerical simulations and fully three-dimensional global stability analyses. For the range of parameters investigated, base flow computations show that the roughness element induces a wake composed of a central low-speed region surrounded by a three-dimensional shear layer and a pair of low- and high-speed stre

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Niu, Han, Jiang Chen, and Hang Xiang. "A New Influence Mechanism of Clocking Effect in Subsonic Compressor." Applied Sciences 13, no. 18 (2023): 10094. http://dx.doi.org/10.3390/app131810094.

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This paper investigates the clocking effect in subsonic compressor element stages and the influence of design parameters on the flow mechanism. We focus on the relationship between the wake-induced separation loss and wake mixing loss and the unsteady mechanism in the wake flow process without considering the transition through several steady and unsteady numerical simulations aimed at a series of subsonic compressor element stages. The simulation results indicate that the performance difference at various indexing positions depends on the relationship between wake mixing loss and wake-induced

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Kyriakides, N. K., E. G. Kastrinakis, S. G. Nychas, and A. Goulas. "Aspects of Flow Structure During a Cylinder Wake-Induced Laminar/Turbulent Transition." AIAA Journal 37, no. 10 (1999): 1197–205. http://dx.doi.org/10.2514/2.613.

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KOYABU, Eitaro, Takashi HONMA, Mitsuki FUJIWARA, Ayumi MITOH, and Eiji SOBU. "J0530204 Studies on Wake-Induced Bypass Transition over Flat Plate Boundary Layer." Proceedings of Mechanical Engineering Congress, Japan 2014 (2014): _J0530204——_J0530204—. http://dx.doi.org/10.1299/jsmemecj.2014._j0530204-.

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Nychas, S. G., A. Goulas, N. K. Kyriakides, and E. G. Kastrinakis. "Aspects of flow structure during a cylinder wake-induced laminar/turbulent transition." AIAA Journal 37 (January 1999): 1197–205. http://dx.doi.org/10.2514/3.14309.

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Tang, Zhan-Qi, and Nan Jiang. "TR PIV Experimental Investigation on Bypass Transition Induced by a Cylinder Wake." Chinese Physics Letters 28, no. 5 (2011): 054702. http://dx.doi.org/10.1088/0256-307x/28/5/054702.

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Lee, H., K. Hourigan, and M. C. Thompson. "Vortex-induced vibration of a neutrally buoyant tethered sphere." Journal of Fluid Mechanics 719 (February 19, 2013): 97–128. http://dx.doi.org/10.1017/jfm.2012.634.

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AbstractA combined numerical and experimental study examining vortex-induced vibration (VIV) of a neutrally buoyant tethered sphere has been undertaken. The study covered the Reynolds-number range $50\leq \mathit{Re}\lesssim 12\hspace{0.167em} 000$, with the numerical ($50\leq \mathit{Re}\leq 800$) and experimental ($370\leqslant \mathit{Re}\lesssim 12\hspace{0.167em} 000$) ranges overlapping. Neutral buoyancy was chosen to eliminate one parameter, i.e. the influence of gravity, on the VIV behaviour, although, of course, the effect of added mass remains. The tether length was also chosen to be

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ROWLEY, CLARENCE W., TIM COLONIUS, and AMIT J. BASU. "On self-sustained oscillations in two-dimensional compressible flow over rectangular cavities." Journal of Fluid Mechanics 455 (March 25, 2002): 315–46. http://dx.doi.org/10.1017/s0022112001007534.

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Numerical simulations are used to investigate the resonant instabilities in two-dimensional flow past an open cavity. The compressible Navier–Stokes equations are solved directly (no turbulence model) for cavities with laminar boundary layers upstream. The computational domain is large enough to directly resolve a portion of the radiated acoustic field, which is shown to be in good visual agreement with schlieren photographs from experiments at several different Mach numbers. The results show a transition from a shear-layer mode, primarily for shorter cavities and lower Mach numbers, to a wake

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Lu, Yuhan, Zaijie Liu, Teng Zhou, and Chao Yan. "Stability analysis of roughness-disturbed boundary layer controlled by wall-blowing." Physics of Fluids 34, no. 10 (2022): 104114. http://dx.doi.org/10.1063/5.0117405.

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Roughness-induced transition control is of considerable importance for high-speed vehicles. In this paper, the instability of a roughness-disturbed boundary layer controlled by spanwise-uniform wall-blowing is investigated through BiGlobal and three-dimensional parabolized stability equation (PSE-3D) analysis. Without wall-blowing, symmetric and antisymmetric unstable modes are observed when using BiGlobal analysis, with PSE-3D analysis suggesting that the symmetric mode is the dominant instability. Both modes are associated with the instability of the entire separated shear layer behind the r

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Shuang, Sun, Li Wei, Lu Xin’gen, Zhang Yanfeng, Zhu Junqiang, and Tong Guoxiang. "A Comparison of the Wake Effects Generated by the Biased Triangle Bar and Traditional Cylinder Bar to the Boundary Layer on Suction Surface of LPT Blade." International Journal of Turbo & Jet-Engines 37, no. 2 (2020): 153–66. http://dx.doi.org/10.1515/tjj-2017-0017.

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AbstractConsidering the asymmetry of the low pressure turbine blade (LPT) wake at a low Reynolds number, the influence of asymmetric wakes which are similar to LPT wakes on the boundary layer of downstream blade rows in the near field is studied in the present paper, in order to increase wake flow prediction accuracy of the downstream blade without increasing the difficulty of the experiment or calculation load. Packb high-lift LPT airfoil was studied with CFX software. Following the analysis of the similarities between the wake generated by the cylinder bar and the triangle bar and the LPT bl

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Ameri, A. A., and A. Arnone. "Transition Modeling Effects on Turbine Rotor Blade Heat Transfer Predictions." Journal of Turbomachinery 118, no. 2 (1996): 307–13. http://dx.doi.org/10.1115/1.2836641.

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The effect of transition modeling on the heat transfer predictions from rotating turbine blades was investigated. Three-dimensional computations using a Reynolds-averaged Navier–Stokes code were performed. The code utilized the Baldwin–Lomax algebraic turbulence model, which was supplemented with a simple algebraic model for transition. The heat transfer results obtained on the blade surface and the hub endwall were compared with experimental data for two Reynolds numbers and their corresponding rotational speeds. The prediction of heat transfer on the blade surfaces was found to improve with

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Fan, S., and B. Lakshminarayana. "Computation and Simulation of Wake-Generated Unsteady Pressure and Boundary Layers in Cascades: Part 1—Description of the Approach and Validation." Journal of Turbomachinery 118, no. 1 (1996): 96–108. http://dx.doi.org/10.1115/1.2836612.

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The unsteady pressure and boundary layers on a turbomachinery blade row arising from periodic wakes due to upstream blade rows are investigated in this paper. A time-accurate Euler solver has been developed using an explicit four-stage Runge–Kutta scheme. Two-dimensional unsteady nonreflecting boundary conditions are used at the inlet and the outlet of the computational domain. The unsteady Euler solver captures the wake propagation and the resulting unsteady pressure field, which is then used as the input for a two-dimensional unsteady boundary layer procedure to predict the unsteady response

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Park, Tae-Choon, Shin-Hyoung Kang, and Woo-Pyung Jeon. "Wake-Induced Boundary Layer Transition on an Airfoil at Moderate Free-Stream Turbulence." Transactions of the Korean Society of Mechanical Engineers B 30, no. 9 (2006): 921–28. http://dx.doi.org/10.3795/ksme-b.2006.30.9.921.

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