Relevant bibliographies by topics / Boundary-layer transition

Contents

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

Academic literature on the topic 'Boundary-layer transition'

Author: Grafiati
Published: 4 June 2021
Last updated: 6 September 2023

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Journal articles on the topic "Boundary-layer transition"

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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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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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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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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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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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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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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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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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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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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Dissertations / Theses on the topic "Boundary-layer transition"

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Yuile, Adam. "Swept boundary layer transition." Thesis, University of Liverpool, 2013. http://livrepository.liverpool.ac.uk/14613/.

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Boundary layer transition has been investigated for incompressible three-dimensional mean flows on a flat plate with a 60° swept leading edge for a nominally zero, a positive, and a negative pressure gradient for three freestream turbulence intensities using a low speed blower tunnel with a 1.22 x 0.61 m working section at the University of Liverpool. The freestream turbulence intensities were generated using grids upstream of the leading edge, producing turbulence levels of approximately 0.2 %, 1.25 % and 3.25 %. For each of these nine (3 x 3) test cases detailed boundary layer traverses were obtained at ten streamwise measurement stations, at a fixed spanwise location, using single-wire constant temperature hot-wire anemometry techniques and digital signal processing. The location for the onset and end of transition was obtained for each case, in terms of distance from the leading edge and local momentum thickness Reynolds number. These results are compared with the 2-D unswept empirical transition correlations of Abu-Ghannam and Shaw (1980) and the differences in the results between the two flows are highlighted. It was found that transition starts and ends earlier than for similar unswept flows, complementing the transition observations of Gray (1952) for swept wings. Further to this the receptivity of the swept boundary layers to freestream turbulence (in the bypass transition regime) was determined by comparing near wall and local freestream spectra, for the pre-transitional boundary layers. These experimental results were compared with numerical predictions from a fourth order accurate computational fluid dynamics method which considered a multitude of perturbation waveforms. This numerical approach was also able to identify the waveform frequency and orientation combinations which drive receptivity in swept boundary layer transition and indicate the manner in which receptivity scales with momentum thickness Reynolds number. It was found that the most receptive waveforms correspond to the streamwise streaks which are frequently observed in flow visualisations and direct numerical simulation studies of pre-transitional boundary layers. Additionally it was also found that the numerical receptivities to freestream turbulence were highest for the positive pressure gradient and, in contrast, lowest for the negative pressure gradient – a similar finding to that in 2-D boundary layers. Transition was seen to commence prior to the advent of the intended non-zero pressure gradients in the experiments and thus direct comparisons are not strictly available. The results obtained, and synthesis undertaken for this thesis, contribute towards an improved understanding of the transition process, particularly with respect to receptivity, in regard to flat plates with swept leading edges in various pressure gradients and highlight the differences between swept and unswept flows. Furthermore, additional avenues have been identified for future work on more complicated topologies where potential problems have also been highlighted.
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Riley, S. "Three-dimensional boundary layer transition." Thesis, University of Liverpool, 1985. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.356291.

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Gardiner, I. D. "Transition in boundary layer flows." Thesis, University of Abertay Dundee, 1987. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.376973.

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An experimental investigation of transition in boundary layer flows under the influence of various freestream conditions is described. Velocity profiles are obtained automatically by means of a stepper-motor driven traverse mechanism which carries a hot wire probe connected to a constant temperature anemometer and associated instrumentation. This was achieved by use of a data acquisition and control facility centred around a microcomputer with a Eurocard rack mounted extension. The automatic boundary layer traverse is software controlled and the data obtained is stored in a disc file for subsequent analysis and graphical display. As an integral part of this facility a successful method of obtaining reliable intermittency values from a hot wire signal was developed. The influence of freestream turbulence and pressure gradient upon transition within a boundary layer developing on a flat plate is elucidated by a series of controlled experiments. From the data accumulated, the concept of statistical similarity in transition regions is extended to include moderate non-zero pressure gradients, with the streamwise mean intermittency distribution described by the normal distribution function. An original correlation which accounts for the influence of freestream turbulence in zero pressure gradient flows, and the combined influence of freestream turbulence and pressure gradient in adverse pressure gradient flows, on the transition length Reynolds number R, is presented. (The limited amount of favourable pressure gradient data precluded the extension of the correlation to include favourable pressure gradient flows). A further original contribution was the derivation of an intermittency weighted function which describes the development of the boundary layer energy thickness through the transition region. A general boundary layer integral prediction scheme based on existing established integral techniques for the laminar and turbulent boundary layers with an intermittency modelled transition region, has been developed and applied successfully to a range of test data.
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Grimaldi, Margaret Elizabeth. "Roughness-induced boundary layer transition." Thesis, Massachusetts Institute of Technology, 1994. http://hdl.handle.net/1721.1/47353.

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Högberg, Markus. "Optimal Control of Boundary Layer Transition." Doctoral thesis, KTH, Mechanics, 2001. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-3245.

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Högberg, Markus. "Optimal control of boundary layer transition /." Stockholm, 2001. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-3245.

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Berlin, Stellan. "Oblique waves in boundary layer transition." Doctoral thesis, Stockholm, 1998. http://www.lib.kth.se/abs98/berl0529.pdf.

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Hachem, Farouk H. "Boundary layer transition on concave surfaces." Thesis, University of Liverpool, 1989. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.279702.

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Leoutsakos, George. "Boundary layer transition on concave surfaces." Thesis, Imperial College London, 1987. http://hdl.handle.net/10044/1/47060.

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Ozkan, Musa. "Boundary layer transition over rotating disks." Thesis, University of Warwick, 2016. http://wrap.warwick.ac.uk/87170/.

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This thesis summarizes results of a combined numerical and experimental study investigating the effects of surface roughness, and of the geometry of the ow domain (confinement) on the boundary{layer transition over rotating disks. Numerically, a three{dimensional enclosed cavity ow in a rotor{stator flow configuration is simulated. The effects induced by surface roughness of the rotor disk and the effects induced by the stator geometry enclosing the ow domain are investigated. The steady{state velocity pro les of the boundary{layer ow on the rotating disk are obtained, subjected to a linear stability analysis and compared to relevant data from the literature. Experimentally, the ow over rotating disks is studied for smooth disk surfaces and for disks with concentric grooves representing distributed roughness. The disks are mounted submerged inside a water {filled tank. Due to the surrounding perimeter wall of the tank and the liquid surface this arrangement resembles the classic rotor{stator flow configuration. Comprehensive measurements of the boundary{layer ow and its laminar{turbulent transition were performed by means of an hot{ lm anemometer. The computational results suggest that, for the rotor{stator ow investigated, the roughness{induced effects are very similar to the geometry{induced effects, both in nature and magnitude. This suggests that it may be di cult to distinguish between both effects in experiments where the ow domain is restricted. Nevertheless, in comparison to previous hot{ lm measurements employing the same experimental facility, the data of the current study have been significantly improved by means of introducing a new calibration technique. The new experimental data discussed here confirm recent theoretical results of our research group in that they corroborate that an increase in the roughness level can reduce the number of stationary vortices and also stabilize the Type{I (cross{ ow) instability mode. However, the detailed analysis of the experimental data, in comparison to the theoretically predicted magnitude of the roughness{induced and the geometry{induced effects, reveal that future studies would greatly bene t from the availability of a new air{based rotating{disk apparatus.
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Books on the topic "Boundary-layer transition"

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Narasimha, R. Modeling the transitional boundary layer. Hampton, Va: Institute for Computer Applications in Science and Engineering, 1990.

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O'Hare, J. E. A nonperturbing boundary-layer transition detector. Arnold Air Force Station, Tenn: Arnold Engineering Development Center, 1985.

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Herbert, Th. Boundary-layer transition - analysis and prediction revisted. Washington, D. C: American Institute of Aeronautics and Astronautics, 1991.

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Institute for Computer Applications in Science and Engineering., ed. Modelling the transitional boundary layer. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, Institute for Computer Applications in Science and Engineering, 1990.

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Fasel, Hermann F. Numerical simulation of nonlinear receptivity in boundary layer transition. Tucson, Ariz: University of Arizona, Engineering Experiment Station, 1990.

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Holmes, Bruce J. Advanced boundary layer transition measurement methods for flight applications. New York: American Institute of Aeronautics and Astronautics, 1986.

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Bertolotti, Fabio P. Simulation of boundary-layer transition: receptivity to spike stage. Hampton, Va: Institute for Computer Applications in Science and Engineering, 1992.

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United States. National Aeronautics and Space Administration., ed. The role of nonlinear critical layers in boundary layer transition. [Washington, D.C: National Aeronautics and Space Administration, 1995.

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Goldstein, Marvin E. The effect of nonlinear critical layers on boundary layer transition. [Washington, D.C: National Aeronautics and Space Administration, 1995.

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J, Holmes Bruce, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch., eds. Flight-measured laminar boundary-layer transition phenomena including stability theory analysis. [Washington, D.C.]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1985.

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Book chapters on the topic "Boundary-layer transition"

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Stetson, Kenneth F. "Hypersonic Boundary-Layer Transition." In Advances in Hypersonics, 324–417. Boston, MA: Birkhäuser Boston, 1992. http://dx.doi.org/10.1007/978-1-4612-0379-7_7.

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Gaudet, L. "Visualisation of Boundary Layer Transition." In Laminar-Turbulent Transition, 699–704. Berlin, Heidelberg: Springer Berlin Heidelberg, 1990. http://dx.doi.org/10.1007/978-3-642-84103-3_66.

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Kachanov, Yury S. "Routes of Boundary-Layer Transition." In Solid mechanics and its applications, 95–104. Dordrecht: Springer Netherlands, 2006. http://dx.doi.org/10.1007/978-1-4020-4150-1_9.

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Smith, Frank T. "Nonlinear Breakdowns in Boundary Layer Transition." In Laminar-Turbulent Transition, 81–91. Berlin, Heidelberg: Springer Berlin Heidelberg, 1990. http://dx.doi.org/10.1007/978-3-642-84103-3_6.

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Arnal, D., F. Vignau, and J. C. Juillen. "Boundary Layer Tripping in Supersonic Flow." In Laminar-Turbulent Transition, 669–79. Berlin, Heidelberg: Springer Berlin Heidelberg, 1990. http://dx.doi.org/10.1007/978-3-642-84103-3_62.

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Levchenko, V. Ya, and V. A. Scherbakov. "On 3-D Boundary Layer Receptivity." In Laminar-Turbulent Transition, 525–32. Berlin, Heidelberg: Springer Berlin Heidelberg, 1995. http://dx.doi.org/10.1007/978-3-642-79765-1_62.

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Malik, M. R. "Hypersonic Boundary-Layer Receptivity and Stability." In Laminar-Turbulent Transition, 409–14. Berlin, Heidelberg: Springer Berlin Heidelberg, 2000. http://dx.doi.org/10.1007/978-3-662-03997-7_61.

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Hanifi, A., and D. S. Henningson. "Stability of Boundary Layer Flows." In Transition, Turbulence and Combustion Modelling, 51–103. Dordrecht: Springer Netherlands, 1999. http://dx.doi.org/10.1007/978-94-011-4515-2_2.

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Mankbadi, Reda R. "Later Stages of Boundary-Layer Transition." In Transition, Turbulence, and Noise, 51–82. Boston, MA: Springer US, 1994. http://dx.doi.org/10.1007/978-1-4615-2744-2_3.

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Lysenko, V. I. "High-Speed Boundary-Layer Stability and Transition." In Laminar-Turbulent Transition, 213–20. Berlin, Heidelberg: Springer Berlin Heidelberg, 1995. http://dx.doi.org/10.1007/978-3-642-79765-1_25.

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Conference papers on the topic "Boundary-layer transition"

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Roberts, S. K., and M. I. Yaras. "Modeling of Boundary-Layer Transition." In ASME Turbo Expo 2004: Power for Land, Sea, and Air. ASMEDC, 2004. http://dx.doi.org/10.1115/gt2004-53664.

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This paper presents a mathematical model for predicting the rate of turbulent spot production. In this model, attached- and separated-flow transition are treated in a unified manner, and the boundary layer shape factor is identified as the parameter with which the spot production rate correlates. The model is supplemented by several correlations to allow for its practical use in the prediction of the length of the transition zone. Secondly, the paper presents a model for the prediction of the location of transition inception in separation-bubbles. The model improves on the accuracy of existing alternatives, and is the first to account for the effects of surface roughness.
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Woodruff, Stephen. "WMLES of Boundary-Layer Transition." In AIAA Scitech 2021 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2021. http://dx.doi.org/10.2514/6.2021-1841.

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Johnson, Mark W., and Ali H. Ercan. "A Boundary Layer Transition Model." In ASME 1996 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1996. http://dx.doi.org/10.1115/96-gt-444.

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A new boundary layer transition model is presented which relates the velocity fluctuations near the wall to the formation of turbulent spots. A relationship for the near wall velocity frequency spectra is also established, which indicates an increasing bias towards low frequencies as the skin friction coefficient for the boundary layer decreases. This result suggests that the dependence of transition on the turbulent length scale is greatest at low freestream turbulence levels. This transition model is incorporated in a conventional boundary layer integral technique and is used to predict eight of the ERCOFTAC test cases. Three of these test cases are for nominally zero pressure gradient and the remaining five are for a pressure distribution typical of an aft loaded turbine blade. The model is demonstrated to predict the development of the boundary layer through transition reasonably accurately for all the test cases. The sensitivity of start of transition to the turbulent length scale at low freestream turbulence levels is also demonstrated.
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Victorino, Victor B., Felipe O. Aguirre, and Marcello A. Medeiros. "Gap induced boundary layer transition." In AIAA AVIATION 2023 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2023. http://dx.doi.org/10.2514/6.2023-3997.

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Becker, Stefan, Donald M. McEligot, Edmond Walsh, and Eckart Laurien. "Criteria for Boundary Layer Transition." In ASME 2011 Turbo Expo: Turbine Technical Conference and Exposition. ASMEDC, 2011. http://dx.doi.org/10.1115/gt2011-45110.

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New results are deduced to assess the validity of proposed transition indicators when applied to situations other than boundary layers on smooth surfaces. The geometry employed utilizes a two-dimensional square rib to disrupt the boundary layer flow. The objective is to determine whether some available criteria are consistent with the present measurements of laminar recovery and transition for the flow downstream of this rib. For the present data — the proposed values of thresholds for transition in existing literature that are based on the freestream turbulence level at the leading edge are not reached in the recovering laminar run but they are not exceeded in the transitioning run either. Of the pointwise proposals examined, values of the suggested quantity were consistent for three of the criteria; that is, they were less than the threshold in laminar recovery and greater than it in the transitioning case.
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Malik, Mujeeb, and Mujeeb Malik. "Boundary-layer transition prediction toolkit." In 28th Fluid Dynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1997. http://dx.doi.org/10.2514/6.1997-1904.

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Fasihfar, Ahmad, and Mark W. Johnson. "An Improved Boundary Layer Transition Correlation." 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-245.

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The influence of pressure gradient and freestream turbulence level on boundary layer transition has been studied experimentally using hot wire instrumentation and digital signal processing and analysis. An established transition correlation and recent transition model were found to give acceptable prediction of the experimental results. The digital system was used to conditionally sample the transitional boundary layer data and hence to determine the mean and fluctuating velocity profiles for the laminar and turbulent parts of the boundary layer separately. The turbulent portions were found to correlate well with fully developed turbulent boundary layer profiles, but the laminar portion profiles deviated considerably from those typical of a laminar boundary layer.
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de Lange, H. C., and Rob J. M. Bastiaans. "DNS/LES of boundary layer transition." In International Heat Transfer Conference 12. Connecticut: Begellhouse, 2002. http://dx.doi.org/10.1615/ihtc12.1370.

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Reshotko, Eli. "Boundary layer instability, transition and control." In 32nd Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1994. http://dx.doi.org/10.2514/6.1994-1.

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Berry, Scott, Thomas Horvath, Brian Hollis, H. Hamilton, II, and Richard Thompson. "X-33 hypersonic boundary layer transition." In 33rd Thermophysics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1999. http://dx.doi.org/10.2514/6.1999-3560.

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Reports on the topic "Boundary-layer transition"

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Miró Miró, Fernando. Boundary-layer Stability and Transition. Von Karman Institute for Fluid Dynamics, 2020. http://dx.doi.org/10.35294/tm58.

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Stetson, Kenneth F. Comments on Hypersonic Boundary-Layer Transition. Fort Belvoir, VA: Defense Technical Information Center, September 1990. http://dx.doi.org/10.21236/ada227242.

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Kimmel, Roger L., Matthew P. Borg, Joseph S. Jewell, James H. Miller, and Dinesh Prabhu. HIFiRE-5 Boundary Layer Transition and HIFiRE-1 Shock Boundary Layer Interaction. Fort Belvoir, VA: Defense Technical Information Center, October 2015. http://dx.doi.org/10.21236/ada623564.

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Reed, Helen L. Navier-Stokes Simulation of Boundary-Layer Transition. Fort Belvoir, VA: Defense Technical Information Center, May 1990. http://dx.doi.org/10.21236/ada226351.

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Kimmel, Roger L., and J. Poggie. Three-Dimensional Hypersonic Boundary Layer Stability and Transition. Fort Belvoir, VA: Defense Technical Information Center, December 1997. http://dx.doi.org/10.21236/ada417303.

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Kuntz, D. W., A. C. Wilken, and J. L. Payne. Analysis of the photodiode boundary layer transition indicator. Office of Scientific and Technical Information (OSTI), January 1994. http://dx.doi.org/10.2172/10124071.

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Doyle, John C. Robustness and Transition to Turbulence in Boundary Layer Flows. Fort Belvoir, VA: Defense Technical Information Center, March 2001. http://dx.doi.org/10.21236/ada405611.

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Lauchie, G. C., and S. Park. Low-Wavenumber Wall Pressure Fluctuations due to Boundary-Layer Transition. Fort Belvoir, VA: Defense Technical Information Center, May 2000. http://dx.doi.org/10.21236/ada379540.

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Beierholm, Amy K., Ivett Leyva, S. J. Laurence, J. Jewel, and H. G. Hornung. Transition Delay in a Hypervelocity Boundary Layer using Nonequilibrium CO2 Injection. Fort Belvoir, VA: Defense Technical Information Center, October 2008. http://dx.doi.org/10.21236/ada503215.

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Kuntz, D. W., A. C. Wilken, and J. L. Payne. Analysis of the photodiode boundary layer transition indicator. LDRD final report. Office of Scientific and Technical Information (OSTI), June 1994. http://dx.doi.org/10.2172/10163751.

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