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Journal articles on the topic 'Boundary-layer transition'

Author: Grafiati

Published: 4 June 2021

Last updated: 6 September 2023

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1

Zhao, Yongling, Chengwang Lei, and John C. Patterson. "The K-type and H-type transitions of natural convection boundary layers." Journal of Fluid Mechanics 824 (July 5, 2017): 352–87. http://dx.doi.org/10.1017/jfm.2017.354.

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The K-type and H-type transitions of a natural convection boundary layer of a fluid of Prandtl number 7 adjacent to an isothermally heated vertical surface are investigated by means of three-dimensional direct numerical simulation (DNS). These two types of transitions refer to different flow features at the transitional stage from laminar to turbulence caused by two different types of perturbations. To excite the K-type transition, superimposed Tollmien–Schlichting (TS) and oblique waves of the same frequency are introduced into the boundary layer. It is found that a three-layer longitudinal vortex structure is present in the boundary layer undergoing the K-type transition. The typical aligned $\wedge$-shaped vortices characterizing the K-type transition are observed for the first time in pure natural convection boundary layers. For exciting the H-type transition, superimposed TS and oblique waves of different frequencies, with the frequency of the oblique waves being half of the frequency of the TS waves, are introduced into the boundary layer. Unlike the three-layer longitudinal vortex structure observed in the K-type transition, a double-layer longitudinal vortex structure is observed in the boundary layer undergoing the H-type transition. The successively staggered $\wedge$-shaped vortices characterizing the H-type transition are also observed in the downstream boundary layer. The staggered pattern of $\wedge$-shaped vortices is considered to be caused by temporal modulation of the TS and oblique waves. Interestingly the flow structures of both the K-type and H-type transitions observed in the natural convection boundary layer are qualitatively similar to those observed in Blasius boundary layers. However, an analysis of turbulence energy production suggests that the turbulence energy production by buoyancy rather than Reynolds stresses dominates the K-type and H-type transitions. In contrast, the turbulence energy production by Reynolds stresses is the only factor contributing to the transition in Blasius boundary layers.

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2

Wu, Xiaohua, Parviz Moin, and Jean-Pierre Hickey. "Boundary layer bypass transition." Physics of Fluids 26, no. 9 (September 2014): 091104. http://dx.doi.org/10.1063/1.4893454.

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3

Sandu, I., B. Stevens, and R. Pincus. "On the transitions in marine boundary layer cloudiness." Atmospheric Chemistry and Physics Discussions 9, no. 6 (November 5, 2009): 23589–622. http://dx.doi.org/10.5194/acpd-9-23589-2009.

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Abstract. Satellite observations and meteorological reanalysis are used to examine the transition from unbroken sheets of stratocumulus to fields of scattered cumulus, and the processes controlling them, in four subtropical ocean basins. A Lagrangian analysis suggests that both the transition, defined as the temporal evolution in cloudiness, and the processes driving the transition, are quite similar among the oceanic basins. The transitions in marine boundary layer cloudiness are an extremely persistent feature of the subtropical ocean's environment, so that the transitions' characteristics obtained by documenting the flow of thousands of individual air masses are well reproduced by the mean (or climatological) fields of the different data sets. This opens new opportunities for future observations and modeling studies of these transitions.

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4

Tanaka, Hitoshi, Nguyen Xuan Tinh, and Ahmad Sana. "Tsunami Damping due to Bottom Friction Considering Flow Regime Transition and Depth-Limitation in a Boundary Layer." Journal of Marine Science and Engineering 10, no. 10 (October 5, 2022): 1433. http://dx.doi.org/10.3390/jmse10101433.

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According to recent investigations on bottom boundary layer development under tsunami, a wave boundary can be observed even at the water depth of 10 m, rather than a steady flow type boundary layer. Moreover, it has been surprisingly reported that the tsunami boundary layer remains laminar in the deep-sea area. For this reason, the bottom boundary layer under tsunami experiences two transitional processes during the wave shoaling: (1) flow regime transition in a wave-motion boundary layer from laminar to the turbulent regime, and (2) transition from non-depth-limited (wave boundary layer) to depth-limited boundary layer (steady flow boundary layer). In the present study, the influence of these two transition processes on tsunami wave height damping has been investigated using a wave energy flux model. Moreover, a difference of calculation results by using the conventional steady flow friction coefficient was clarified.

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5

Pinson, Mark W., and Ting Wang. "Effect of Two-Scale Roughness on Boundary Layer Transition Over a Heated Flat Plate: Part 2—Boundary Layer Structure." Journal of Turbomachinery 122, no. 2 (February 1, 1999): 308–16. http://dx.doi.org/10.1115/1.555454.

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Velocity and temperature measurements made within transitional boundary layers over a surface roughened by two roughness scales were examined. The variation of intermittency through the transition region was shown to be consistent with a smooth-wall model of transition, but the prediction of transition onset was not well represented by momentum thickness for cases with strong surface disturbances. During transition, distributed roughness was shown to reduce the growth of velocity fluctuation, possibly through stronger dissipation, and to enhance wallward transport of momentum significantly without a corresponding increase in thermal transport. The step change between the two roughness scales was shown to notably affect boundary layer behavior. Spectral analysis supported the hypothesis in Part 1 that the separated region downstream of the step shed vortices into the downstream flow. The wavelet analysis suggested that transition over rough surfaces may be in bypass mode because the disturbances were shown to be amplified in a broad spectral band. [S0889-504X(00)00302-0]

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6

Sandu, I., B. Stevens, and R. Pincus. "On the transitions in marine boundary layer cloudiness." Atmospheric Chemistry and Physics 10, no. 5 (March 8, 2010): 2377–91. http://dx.doi.org/10.5194/acp-10-2377-2010.

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Abstract. Satellite observations and meteorological reanalysis are used to examine the transition from unbroken sheets of stratocumulus to fields of scattered cumulus, and the processes controlling them, in four subtropical oceans. A Lagrangian analysis suggests that both the transition, defined as the temporal evolution in cloudiness, and the processes driving the transition, are quite similar among the subtropical oceans. The increase in sea surface temperature and the associated decrease in lower tropospheric stability appear to play a far more important role in cloud evolution than other factors including changes in large scale divergence and upper tropospheric humidity. During the summer months, the transitions in marine boundary layer cloudiness appear so systematically that their characteristics obtained by documenting the flow of thousands of individual air masses are well reproduced by the mean (or climatological) fields of the different data sets. This highlights interesting opportunities for future observational and modeling studies of these transitions.

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7

Šimurda, David, Jindřich Hála, Martin Luxa, and Tomáš Radnic. "Optical and Hot-Film Measurements of the Boundary Layer Transition on a Naca Airfoil." E3S Web of Conferences 345 (2022): 01011. http://dx.doi.org/10.1051/e3sconf/202234501011.

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This study explores the possibilities of identifying position of a boundary layer transition using hot film measurements complemented by classical optical methods i.e. interferometry and schlieren method. The subject of the measurement is a NACA 0010-64 airfoil with varying leading edge surface quality corresponding to smooth surface and rough surface with Ra ~ 50 and Ra ~ 100. Measurements are performed at several subsonic regimes and a transonic regime. Despite several shortcomings of the experimental setup, the method proved to be useful in providing information on the boundary layer transition. Measurements show that in the case of smooth leading edge, the onset of the boundary layer transition shifts upstream with increasing inlet Mach number and the major portion of the boundary layer is transitional. This is in accordance with other published results on the boundary layer transition on this kind of airfoils [1]. In all cases with the rough leading edge, the complete transition takes place on the rough portion of the surface already.

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8

Berry, Scott, Kamran Daryabeigi, Kathryn Wurster, and Robert Bittner. "Boundary-Layer Transition on X-43A." Journal of Spacecraft and Rockets 47, no. 6 (November 2010): 922–34. http://dx.doi.org/10.2514/1.45889.

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9

Berry, Scott A., Thomas J. Horvath, Brian R. Hollis, Rick A. Thompson, and H. Harris Hamilton. "X-33 Hypersonic Boundary-Layer Transition." Journal of Spacecraft and Rockets 38, no. 5 (September 2001): 646–57. http://dx.doi.org/10.2514/2.3750.

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10

MATSUYAMA, Shingo. "DNS of Hypersonic Boundary Layer Transition." Journal of the Visualization Society of Japan 41, no. 162 (2021): 13–14. http://dx.doi.org/10.3154/jvs.41.162_13.

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11

Liepmann, Hans W. "Boundary Layer Transition: The Early Days." Applied Mechanics Reviews 50, no. 2 (February 1, 1997): R1—R4. http://dx.doi.org/10.1115/1.3101691.

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12

Healey, J. J. "Spatial chaos in boundary layer transition." Applied Scientific Research 51, no. 1-2 (June 1993): 49–53. http://dx.doi.org/10.1007/bf01082513.

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13

Mahrt, L. "The early evening boundary layer transition." Quarterly Journal of the Royal Meteorological Society 107, no. 452 (July 6, 2007): 329–43. http://dx.doi.org/10.1002/qj.49710745205.

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14

Walsh, Edmond J., Kevin P. Nolan, Donald M. McEligot, Ralph J. Volino, and Adrian Bejan. "Conditionally-Sampled Turbulent and Nonturbulent Measurements of Entropy Generation Rate in the Transition Region of Boundary Layers." Journal of Fluids Engineering 129, no. 5 (January 8, 2007): 659–64. http://dx.doi.org/10.1115/1.2717622.

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Conditionally-sampled boundary layer data for an accelerating transitional boundary layer have been analyzed to calculate the entropy generation rate in the transition region. By weighing the nondimensional dissipation coefficient for the laminar-conditioned-data and turbulent-conditioned-data with the intermittency factor γ the average entropy generation rate in the transition region can be determined and hence be compared to the time averaged data and correlations for steady laminar and turbulent flows. It is demonstrated that this method provides, for the first time, an accurate and detailed picture of the entropy generation rate during transition. The data used in this paper have been taken from detailed boundary layer measurements available in the literature. This paper provides, using an intermittency weighted approach, a methodology for predicting entropy generation in a transitional boundary layer.

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15

Nolan, Kevin P., Edmond J. Walsh, Donald M. McEligot, and Ralph J. Volino. "Predicting Entropy Generation Rates in Transitional Boundary Layers Based on Intermittency." Journal of Turbomachinery 129, no. 3 (July 25, 2006): 512–17. http://dx.doi.org/10.1115/1.2720488.

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Prediction of thermodynamic loss in transitional boundary layers is typically based on time-averaged data only. This approach effectively ignores the intermittent nature of the transition region. In this work laminar and turbulent conditionally sampled boundary layer data for zero pressure gradient and accelerating transitional boundary layers have been analyzed to calculate the entropy generation rate in the transition region. By weighting the nondimensional dissipation coefficient for the laminar conditioned data and turbulent conditioned data with the intermittency factor, the entropy generation rate in the transition region can be determined and compared to the time-averaged data and correlations for laminar and turbulent flow. It is demonstrated that this method provides an accurate and detailed picture of the entropy generation rate during transition in contrast with simple time averaging. The data used in this paper have been taken from conditionally sampled boundary layer measurements available in the literature for favorable pressure gradient flows. Based on these measurements, a semi-empirical technique is developed to predict the entropy generation rate in a transitional boundary layer with promising results.

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16

Johnson, Mark W. "Predicting Transition on Concave Surfaces." Journal of Turbomachinery 129, no. 4 (August 18, 2006): 750–55. http://dx.doi.org/10.1115/1.2720865.

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Boundary layers on concave surfaces differ from those on flat plates due to the presence of Taylor-Goertler (T-G) vortices. These vortices cause momentum transfer normal to the blade’s surface and hence result in a more rapid development of the laminar boundary layer and a fuller profile than is typical of a flat plate. Transition of boundary layers on concave surfaces also occurs at a lower Rex than on a flat plate. Concave surface transition correlations have been formulated previously from experimental data, but they are not comprehensive and are based on relatively sparse data. The purpose of the current work was to attempt to model the physics of both the laminar boundary layer development and transition process in order to produce a transition model suitable for concave surface boundary layers. The development of the laminar boundary layer on a concave surface was modeled by considering the profiles at the upwash and downwash locations separately. The profiles of the boundary layers at these two locations were then combined to successfully approximate the spanwise averaged profile. The ratio of the boundary layer thicknesses at the two locations was found to be as great as 50 and this leads to laminar boundary layer shape factors as low as 1.3 and skin friction coefficients up to 12 times the value for a flat plate laminar boundary layer. Boundary layers therefore grow much more rapidly on concave surfaces than on flat plates. The transition model assumed that transition commenced in the upwash location boundary layer at the same transition inception Reθ observed on a flat plate. Transition at the downwash location then results from the growth of turbulent spots from the upwash location rather than through the initiation of spots. The model showed that initially curvature promotes transition because of the thickened upwash boundary layer, but for strong curvature the T-G vortices effectively stabilize the boundary layer and transition then occurs at a higher Reθ than on a flat plate. Results from the transition model were in broad agreement with experimental observations. The current work therefore provides a basis for the modeling of transition on concave surfaces.

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17

Lauchle, Gerald C. "Hydroacoustics of Transitional Boundary-Layer Flow." Applied Mechanics Reviews 44, no. 12 (December 1, 1991): 517–31. http://dx.doi.org/10.1115/1.3119491.

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Transitional boundary layers exist on surfaces and bodies operating in viscous fluids at speeds such that the critical Reynolds number based on the distance from the leading edge is exceeded. The transition region is composed of a simultaneous mixture of both laminar and turbulent regimes occurring randomly in space and time. The turbulent regimes are known as turbulent spots, they grow rapidly with downstream distance, and they ultimately coalesce to form the beginning of fully-developed turbulent boundary-layer flow. It has been long suspected that such a region of unsteadiness may give rise to local pressure fluctuations and radiated sound that are different from those created by the fully-developed turbulent boundary layer at equivalent Reynolds number. This article reviews the available literature on this subject. The emphasis of this literature is on natural and artificially created transitional boundary layers under mostly incompressible conditions; hence, the word hydroacoustics in the title. The topics covered include the dynamics and local wall pressure fluctuations due to the passage of turbulent spots created in a deterministic way, the pressure fluctuations under transitioning boundary layers where the formation and location of spots are random, and the acoustic radiation from transition and its pre-cursor, the Tollmien-Schlichting waves. The majority of this review is for zero-pressure gradient flat plate flows, but the limited literature on axisymmetric body and plate flows with pressure gradient is included.

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18

Laurien, E., and L. Kleiser. "Numerical simulation of boundary-layer transition and transition control." Journal of Fluid Mechanics 199 (February 1989): 403–40. http://dx.doi.org/10.1017/s002211208900042x.

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The laminar-turbulent transition process in a parallel boundary-layer with Blasius profile is simulated by numerical integration of the three-dimensional incompressible Navier-Stokes equations using a spectral method. The model of spatially periodic disturbances developing in time is used. Both the classical Klebanoff-type and the subharmonic type of transition are simulated. Maps of the three-dimensional velocity and vorticity fields and visualizations by integrated fluid markers are obtained. The numerical results are compared with experimental measurements and flow visualizations by other authors. Good qualitative and quantitative agreement is found at corresponding stages of development up to the one-spike stage. After the appearance of two-dimensional Tollmien-Schlichting waves of sufficiently large amplitude an increasing three-dimensionality is observed. In particular, a peak-valley structure of the velocity fluctuations, mean longitudinal vortices and sharp spike-like instantaneous velocity signals are formed. The flow field is dominated by a three-dimensional horseshoe vortex system connected with free high-shear layers. Visualizations by time-lines show the formation of A-structures. Our numerical results connect various observations obtained with different experimental techniques. The initial three-dimensional steps of the transition process are consistent with the linear theory of secondary instability. In the later stages nonlinear interactions of the disturbance modes and the production of higher harmonics are essential.We also study the control of transition by local two-dimensional suction and blowing at the wall. It is shown that transition can be delayed or accelerated by superposing disturbances which are out of phase or in phase with oncoming Tollmien-Schlichting instability waves, respectively. Control is only effective if applied at an early, two-dimensional stage of transition. Mean longitudinal vortices remain even after successful control of the fluctuations.

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19

Fraser, C. J., M. G. Higazy, and J. S. Milne. "End-Stage Boundary Layer Transition Models for Engineering Calculations." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 208, no. 1 (January 1994): 47–58. http://dx.doi.org/10.1243/pime_proc_1994_208_097_02.

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The paper presents some recent new data on the combined effects of pressure gradient and freestream turbulence level on the onset and length of the latter stages of the boundary layer transition process. Generalized correlations for the transition length Reynolds number are developed from considerations of the non-dimensional turbulent spot formation rate. The optimized correlation is built into a popular linear combination integral computer code to predict the growth of the transitional boundary layer in a number of practical engineering flows.

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20

Kolla, Maureen L., and Jeffrey W. Yokota. "CONTROLLING BOUNDARY LAYER TRANSITION OVER A SEPARATION BUBBLE: A COMPLEX-LAMELLAR APPROACH." Transactions of the Canadian Society for Mechanical Engineering 39, no. 2 (June 2015): 153–69. http://dx.doi.org/10.1139/tcsme-2015-0012.

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In this paper, we develop a complex-lamellar description of the incompressible flow that exists as a boundary layer transitions from a fully developed laminar to fully developed turbulent flow. This complex-lamellar description is coupled to the shape of the universal intermittency distribution and experimental correlations to obtain a boundary layer model of transition. This transition model is used to analyze the effects of several different freestream turbulence levels on the reattachment location and the length of the resulting separation bubbles. Furthermore, we show that at the separation bubble reattachment location, the resulting boundary layer flow is both turbulent and fully developed. Results obtained from this transition model are compared with, and verified by several different DNS simulations.

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21

Gostelow, J. P., and G. J. Walker. "Similarity Behavior in Transitional Boundary Layers Over a Range of Adverse Pressure Gradients and Turbulence Levels." Journal of Turbomachinery 113, no. 4 (October 1, 1991): 617–24. http://dx.doi.org/10.1115/1.2929125.

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Boundary layer transition has been investigated experimentally under low, moderate, and high free-stream turbulence levels and varying adverse pressure gradients. Under high turbulence levels and adverse pressure gradients a pronounced subtransition was present. A strong degree of similarity in intermittency distributions was observed, for all conditions, when the Narasimha procedure for determination of transition inception was used. Effects of free-stream turbulence on the velocity profile are particularly strong for the laminar boundary layer upstream of the transition region. This could reflect the influence of the turbulence on the shear stress distribution throughout the layer and this matter needs further attention. The velocity profiles in wall coordinates undershoot the turbulent wall layer asymptote near the wall over most of the transition region. The rapidity with which transition occurs under adverse pressure gradients produces strong lag effects on the velocity profile; the starting turbulent boundary layer velocity profile may depart significantly from local equilibrium conditions. The practice of deriving integral properties and skin friction for transitional boundary layers by a linear combination of laminar and turbulent values for equilibrium layers is inconsistent with the observed lag effects. The velocity profile responds sufficiently slowly to the perturbation imposed by transition that much of the anticipated drop in form factor will not have occurred prior to the completion of transition. This calls into question both experimental techniques, which rely on measured form factor to characterize transition, and boundary layer calculations, which rely on local equilibrium assumptions in the vicinity of transition.

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22

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 cylinder height from the plate, the physical size of these hairpin-like structures is found to decrease. Some mean flow characteristics, including the streamwise growth of the disturbance energy, in a wake-induced transition resemble those in bypass transition induced by free stream turbulence. Streamwise velocity streaks that are eventually generated in the late stage often undergo sinuous-type oscillations. Similar to other transitional flows, an inclined shear layer in the wall-normal plane is often seen to oscillate and shed vortices. The normalized shedding frequency of these vortices, estimated from the spatial spacing and the convection velocity of these vortices, is found to be independent of the Reynolds number, similar to that in ribbon-induced transition. Although the nature of free stream disturbance in a wake-induced transition and that in a bypass transition are different, the late-stage features including the flow breakdown characteristics of these two transitions appear to be similar.

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23

Skála, Vladislav, and Pavel Antoš. "Boundary Layer Transition by Advese Pressure Gradient." EPJ Web of Conferences 269 (2022): 01057. http://dx.doi.org/10.1051/epjconf/202226901057.

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For some cases of diferrent of boundary layer development conditions (roughness of surface, turbulence in main flow) by adverse pressure gradient was determined tranzitiom region. Boundary layer Tranzition region was found based on intermittency development of flow inside the boundary layer. Intermitency was evaluated using modiffied TERA method algorithm.

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24

Yang, Rui, Yuxin Zhao, and Lican Wang. "Natural transition of the supersonic streamwise corner flow." Applied Physics Letters 122, no. 12 (March 20, 2023): 123905. http://dx.doi.org/10.1063/5.0131668.

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The laminar-to-turbulence transition of a streamwise corner flow is recognized to occur first at the corner based on the stability analysis, but there is no persuasive experimental evidence to back it up, especially for supersonic flow. In this work, natural transition in a supersonic corner boundary layer has been experimentally studied using a nanoparticle-based planar laser scattering technique. It is inspiring to observe that the natural transition position of the corner boundary layer shows a random behavior among the corner side, flat-plate side, and their combination. Based on an intermittent factor analysis, these stochastic transitions show a dominant preference for transitions occurring near the corner region.

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25

Chokani, Ndaona. "VITA measurements of transition in transitional hypersonic boundary layer flows." Experiments in Fluids 38, no. 4 (February 25, 2005): 440–48. http://dx.doi.org/10.1007/s00348-004-0923-y.

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26

Govindarajan, Rama. "Boundary Layer Stability and Transition to Turbulence." Resonance 26, no. 10 (October 2021): 1403–15. http://dx.doi.org/10.1007/s12045-021-1243-8.

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27

Kimmel, Roger L. "Introduction: Roughness and Hypersonic Boundary-Layer Transition." Journal of Spacecraft and Rockets 45, no. 6 (November 2008): 1089. http://dx.doi.org/10.2514/1.41332.

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28

Kimmel, Roger L., David Adamczak, Allan Paull, Ross Paull, Jeremy Shannon, Robert Pietsch, Myles Frost, and Hans Alesi. "HIFiRE-1 Ascent-Phase Boundary-Layer Transition." Journal of Spacecraft and Rockets 52, no. 1 (January 2015): 217–30. http://dx.doi.org/10.2514/1.a32851.

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29

Nelson, P. A., M. C. M. Wright, and J. L. Rioual. "Automatic Control of Laminar Boundary-Layer Transition." AIAA Journal 35, no. 1 (January 1997): 85–90. http://dx.doi.org/10.2514/2.66.

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30

Stetson, Kenneth F., and Roger L. Kimmel. "Surface temperature effects on boundary-layer transition." AIAA Journal 30, no. 11 (November 1992): 2782–83. http://dx.doi.org/10.2514/3.11300.

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31

Kuntz, David W., and Donald L. Potter. "Boundary-Layer Transition and Hypersonic Flight Testing." Journal of Spacecraft and Rockets 45, no. 2 (March 2008): 184–92. http://dx.doi.org/10.2514/1.29708.

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32

YAN, D. C., Z. ZHANG, H. M. SHI, and Z. L. SUN. "REVERSE TRANSITION OF A TURBULENT BOUNDARY LAYER." Modern Physics Letters B 19, no. 28n29 (December 20, 2005): 1603–6. http://dx.doi.org/10.1142/s0217984905010013.

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Systematic experimental researches on reverse transition in the boundary layer on a heated plate are carried out, and the time-series of instantaneous velocity components and temperature fluctuation are measured, then the Reynolds stress, the production term and absorption term of turbulent energy are presented. From the experimental results, the characteristics and physics mechanism of reverse transition as well as statistical properties of turbulence during reversion are revealed.

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33

Belotserkovskii, O. M., V. A. Zharov, Htun Htun, and Yu I. Khlopkov. "Monte Carlo simulation of boundary layer transition." Computational Mathematics and Mathematical Physics 49, no. 5 (May 2009): 887–92. http://dx.doi.org/10.1134/s0965542509050145.

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34

Lysenko, V. I. "High-speed boundary-layer stability and transition." International Journal of Mechanical Sciences 35, no. 11 (November 1993): 921–33. http://dx.doi.org/10.1016/0020-7403(93)90030-x.

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35

Kachanov, Y. S. "Physical Mechanisms of Laminar-Boundary-Layer Transition." Annual Review of Fluid Mechanics 26, no. 1 (January 1994): 411–82. http://dx.doi.org/10.1146/annurev.fl.26.010194.002211.

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36

Nelson, P. A., M. C. M. Wright, and J. L. Rioual. "Automatic control of laminar boundary-layer transition." AIAA Journal 35 (January 1997): 85–90. http://dx.doi.org/10.2514/3.13467.

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37

TONG, FuLin, JianQiang CHEN, GuoHua TU, GuoLiang XU, JiuFen CHEN, BingBing WAN, XianXu YUAN, and YiFeng ZHANG. "Recent progresses on hypersonic boundary-layer transition." SCIENTIA SINICA Physica, Mechanica & Astronomica 49, no. 11 (May 1, 2019): 114701. http://dx.doi.org/10.1360/sspma-2019-0071.

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38

Wu, Xiaohua, and Paul A. Durbin. "Boundary Layer Transition Induced by Periodic Wakes." Journal of Turbomachinery 122, no. 3 (November 1, 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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39

Patrick, Chris. "Total temperature affects hypersonic boundary layer transition." Scilight 2019, no. 47 (November 22, 2019): 471107. http://dx.doi.org/10.1063/10.0000281.

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40

Christian Wolf, C., Anthony D. Gardner, and Markus Raffel. "Infrared thermography for boundary layer transition measurements." Measurement Science and Technology 31, no. 11 (September 25, 2020): 112002. http://dx.doi.org/10.1088/1361-6501/aba070.

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41

Bowles, R. I., and F. T. Smith. "On boundary-layer transition in transonic flow." Journal of Engineering Mathematics 27, no. 3 (August 1993): 309–42. http://dx.doi.org/10.1007/bf00128969.

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42

Lebiga, V. A. "The boundary layer transition at supersonic velocities." Journal of Applied Mathematics and Mechanics 78, no. 2 (2014): 114–20. http://dx.doi.org/10.1016/j.jappmathmech.2014.07.002.

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43

Kubacki, Slawomir, Daniele Simoni, Davide Lengani, and Erik Dick. "An Extended Version of an Algebraic Intermittency Model for Prediction of Separation-Induced Transition at Elevated Free-Stream Turbulence Level." International Journal of Turbomachinery, Propulsion and Power 5, no. 4 (October 26, 2020): 28. http://dx.doi.org/10.3390/ijtpp5040028.

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An algebraic intermittency model for boundary layer flow transition from laminar to turbulent state, is extended using an experimental data base on boundary layer flows with various transition types and results by large eddy simulation of transition in a separated boundary layer. The originating algebraic transition model functions well for bypass transition in an attached boundary layer under a moderately high or elevated free-stream turbulence level, and for transition by Kelvin–Helmholtz instability in a separated boundary layer under a low free-stream turbulence level. It also functions well for transition in a separated layer, caused by a very strong adverse pressure gradient under a moderately high or elevated free-stream turbulence level. It is not accurate for transition in a separated layer under a moderately strong adverse pressure gradient, in the presence of a moderately high or elevated free-stream turbulence level. The extension repairs this deficiency. Therefore, a sensor function for detection of the front part of a separated boundary layer activates two terms that express the effect of free-stream turbulence on the breakdown of a separated layer, without changing the functioning of the model in other flow regions. The sensor and the breakdown terms use only local variables.

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44

Bertolotti, Fabio P., and Ronald D. Joslin. "Effect of Far-Field Boundary Conditions on Boundary-Layer Transition." Journal of Computational Physics 118, no. 2 (May 1995): 392–95. http://dx.doi.org/10.1006/jcph.1995.1109.

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45

He, Guo-Sheng, Chong Pan, Li-Hao Feng, Qi Gao, and Jin-Jun Wang. "Evolution of Lagrangian coherent structures in a cylinder-wake disturbed flat plate boundary layer." Journal of Fluid Mechanics 792 (March 3, 2016): 274–306. http://dx.doi.org/10.1017/jfm.2016.81.

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Evolution of Lagrangian coherent structures (LCS) in a flat plate boundary layer transition induced by the wake of a circular cylinder is investigated. Both hydrogen bubble visualization and particle image velocimetry (PIV) techniques are used. It is found that downstream of the cylinder, the disturbance in the boundary layer experiences a fast growth followed by a slow decay in the transition. Lagrangian coherent structures are revealed by qualitative hydrogen bubble visualizations and quantitative finite-time Lyapunov exponents (FTLE) fields derived from the PIV data. The evolution of the LCS is considered from the very beginning of the transition up to when the boundary layer becomes fully developed turbulent flow. The mean convection velocity and average inclination angle of the LCS are first extracted from the FTLE fields. The streamwise length of the low-speed streaks seems to increase, while their spanwise distance decreases in the boundary layer transition. Proper orthogonal decomposition (POD) of the PIV data shows that low-speed streaks associated with the hairpin vortices and hairpin packets are the dominant coherent structures close to the wall in the transitional and turbulent boundary layer. The POD modes also reveal a variety of scales in the turbulent boundary layer. Moreover, it is found that large-scale coherent structures can modulate the amplitude of the small-scale ones.

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46

Matsuura, Kazuo, Kotaro Matsui, and Naoki Tani. "Effects of free-stream turbulence on the global pressure fluctuation of compressible transitional flows in a low-pressure turbine cascade." International Journal of Numerical Methods for Heat & Fluid Flow 28, no. 5 (May 8, 2018): 1187–202. http://dx.doi.org/10.1108/hff-06-2017-0253.

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Purpose This paper aims to investigate global pressure fluctuations in compressible transitional flows in a low-pressure turbine cascade because of variations in the free-stream turbulence and its interaction with the boundary layers. Design/methodology/approach Transition process resolving numerical simulations are performed with different types of inflow turbulence. The unsteady three-dimensional fully compressible Navier–Stokes equations are solved using a sixth-order compact difference and a tenth-order filtering method. First, simulations of both K-regime and bypass transitions are conducted for a flat plate boundary layer to validate the use of the filter in computing different transition routes. Second, computations of the cascade flows are conducted. Cases of no free-stream turbulence, isotropic free-stream turbulence of 5 per cent and wakes from an upstream cylinder are compared. For wakes, variations in wake trajectory depending on the cylinder blade relative position are also taken into account. Findings The different transition routes are successfully reproduced by the present method even with strong filtering. When feedback phenomena occur near the trailing edge, high-frequency oscillations dominate in the flow field. Low-frequency oscillations become dominant when the blade boundary layer becomes turbulent. Thus, the effects of the free-stream turbulence and its interaction with the boundary layer appear as changes in the global pressure fluctuation. Originality/value The free-stream turbulence qualitatively affects global pressure fluctuations, which become a medium to convey boundary-layer information away from the cascade.

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Zhao, Yatian, Zhiyuan Shao, and Hongkang Liu. "Aerodisk Effect on Hypersonic Boundary Layer Transition and Heat Transfer of HIFiRE-5 Vehicle." Aerospace 9, no. 12 (November 23, 2022): 742. http://dx.doi.org/10.3390/aerospace9120742.

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The substantial aerodynamic drag and severe aerothermal loads, which are closely related to boundary layer transition, challenge the design of hypersonic vehicles and could be relieved by active methods aimed at drag and heat flux reduction, such as aerodisk. However, the research of aerodisk effects on transitional flows is still not abundant. Based on the improved k-ω-γ transition model, this study investigates the influence of the aerodisk with various lengths on hypersonic boundary layer transition and surface heat flux distribution over HIFiRE-5 configuration under various angles of attack. Certain meaningful analysis and results are obtained: (i) The existence of aerodisk is found to directly trigger separation-induced transition, moving the transition onset near the centerline upstream and widening the transition region; (ii) The maximum wall heat flux could be effectively reduced by aerodisk up to 52.1% and the maximum surface pressure can even be reduced up to 80.4%. The transition shapes are identical, while the variety of growth rates of intermittency are non-monotonous with the increase in aerodisk length. The dilation of region with high heat flux boundary layer is regarded as an inevitable compromise to reducing maximum heat flux and maximum surface pressure. (iii) With the angle of attack rising, first, the transition is postponed and subsequently advanced on the windward surface, which is in contrast to the continuously extending transition region on the leeward surface. This numerical study aims to explore the effects of aerodisk on hypersonic boundary layer transition, enrich the study of hypersonic flow field characteristics and active thermal protection system considering realistic boundary layer transition, and provide references for the excogitation and utilization of hypersonic vehicle aerodisk.

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Schobeiri, M. T., and L. Wright. "Advances in Unsteady Boundary Layer Transition Research, Part I: Theory and Modeling." International Journal of Rotating Machinery 9, no. 1 (2003): 1–9. http://dx.doi.org/10.1155/s1023621x03000010.

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This two-part article presents recent advances in boundary layer research that deal with the unsteady boundary layer transition modeling and its validation. A new unsteady boundary layer transition model was developed based on a universal unsteady intermittency function. It accounts for the effects of periodic unsteady wake flow on the boundary layer transition. To establish the transition model, an inductive approach was implemented; the approach was based on the results of comprehensive experimental and theoretical studies of unsteady wake flow and unsteady boundary layer flow. The experiments were performed on a curved plate at a zero streamwise pressure gradient under a periodic unsteady wake flow, where the frequency of the periodic unsteady flow was varied. To validate the model, systematic experimental investigations were performed on the suction and pressure surfaces of turbine blades integrated into a high-subsonic cascade test facility, which was designed for unsteady boundary layer investigations. The analysis of the experiment's results and comparison with the model's prediction confirm the validity of the model and its ability to predict accurately the unsteady boundary layer transition.

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JACOBS, R. G., and P. A. DURBIN. "Simulations of bypass transition." Journal of Fluid Mechanics 428 (February 10, 2001): 185–212. http://dx.doi.org/10.1017/s0022112000002469.

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Bypass transition in an initially laminar boundary layer beneath free-stream turbulence is simulated numerically. New perspectives on this phenomenon are obtained from the numerical flow fields. Transition precursors consist of long backward jets contained in the fluctuating u-velocity field; they flow backwards relative to the local mean velocity. The jets extend into the upper portion of the boundary layer, where they interact with free-stream eddies. In some locations a free-stream perturbation to the jet shear layer develops into a patch of irregular motion – a sort of turbulent spot. The spot spreads longitudinally and laterally, and ultimately merges into the downstream turbulent boundary layer. Merging spots maintain the upstream edge of the turbulent region. The jets, themselves, are produced by low-frequency components of the free-stream turbulence that penetrate into the laminar boundary layer. Backward jets are a component of laminar region streaks.A method to construct turbulent inflow from Orr–Sommerfeld continuous modes is described. The free-stream turbulent intensity was chosen to correspond with the experiment by Roach & Brierly (1990). Ensemble-averaged numerical data are shown to be in good agreement with laboratory measurements.

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50

Wang, T., T. W. Simon, and J. Buddhavarapu. "Heat Transfer and Fluid Mechanics Measurements in Transitional Boundary Layer Flows." Journal of Engineering for Gas Turbines and Power 107, no. 4 (October 1, 1985): 1007–15. http://dx.doi.org/10.1115/1.3239804.

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Experimental results are presented to document hydrodynamic and thermal development of flat-plate boundary layers undergoing natural transition. Local heat transfer coefficients, skin friction coefficients, and profiles of velocity, temperature, and Reynolds normal and shear stresses are presented. A case with no transition and transitional cases with 0.68 percent and 2.0 percent free-stream disturbance intensities were investigated. The locations of transition are consistent with earlier data. A late-laminar state with significant levels of turbulence is documented. In late-transitional and early-turbulent flows, turbulent Prandtl number and conduction layer thickness values exceed, and the Reynolds analogy factor is less than, values previously measured in fully turbulent flows.

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