Relevant bibliographies by topics / Laminar breakdown

Contents

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

Academic literature on the topic 'Laminar breakdown'

Author: Grafiati
Published: 5 October 2024
Last updated: 31 July 2025

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Journal articles on the topic "Laminar breakdown"

1

Li, Ning, and Qi Hong Zeng. "Direct Numerical Simulation on Transition of an Incompressible Boundary Layer on a Flat Plate." Applied Mechanics and Materials 268-270 (December 2012): 1143–47. http://dx.doi.org/10.4028/www.scientific.net/amm.268-270.1143.

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Direct Numerical Simulation(DNS) was carried out for laminar-turbulent transition of an incompressible boundary layer on a flat plate based on disturbance Navier-Stokes(N-S) equation in spatial mode with Massage Passing Interface(MPI) technology. Study on breakdown mechanism of laminar-turbulent transition was carried on. The effect of mean flow distortion on the process of breakdown in laminar-turbulent transition was investigated. Results indicate that change of instability characteristic of mean flow profile plays a key role during process of breakdown.
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Zhou, Teng, Zaijie Liu, Yuhan Lu, Ying Wang, and Chao Yan. "Direct numerical simulation of complete transition to turbulence via first- and second-mode oblique breakdown at a high-speed boundary layer." Physics of Fluids 34, no. 7 (2022): 074101. http://dx.doi.org/10.1063/5.0094069.

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Complete transition to turbulence via first- and second-mode oblique breakdown in a high-speed boundary layer at Mach 4.5 is studied by direct numerical simulations (DNS) and linear stability theory (LST). The initial frequency and spanwise wavenumbers for both types of oblique breakdown are determined from LST. Then, DNS is employed to study the main features of the two oblique breakdown types in detail, which has rarely been discussed in previous studies. This includes the main flow structures and evolution of various modes during the linear, nonlinear, and breakdown stages, and both differe
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Seifi, Zeinab, Mehrdad Raisee, and Michel J. Cervantes. "Optimal flow control of vortex breakdown in a laminar swirling flow." Journal of Physics: Conference Series 2707, no. 1 (2024): 012129. http://dx.doi.org/10.1088/1742-6596/2707/1/012129.

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Abstract In highly swirling flows, such as hydraulic turbines operating under part-load (PL) conditions, vortex breakdown occurs and performance is impaired. Consequently, it is imperative that mitigation measures are taken. In the present study, a laminar swirling flow with a vortex breakdown at a Reynolds number of 180 is investigated. At the inlet, a swirling velocity profile with a swirl number of 1.095 is set. A stability analysis is conducted to identify unstable modes based on the assumption that vortex breakdown is a global instability. The results indicate that spiral modes with wave
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Kadyirov, A. I., and B. R. Abaydullin. "Vortex Breakdown under Laminar Flow of Pseudoplastic Fluid." Journal of Physics: Conference Series 899 (September 2017): 022009. http://dx.doi.org/10.1088/1742-6596/899/2/022009.

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Kachanov, Yu S. "On the resonant nature of the breakdown of a laminar boundary layer." Journal of Fluid Mechanics 184 (November 1987): 43–74. http://dx.doi.org/10.1017/s0022112087002805.

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The first part of this paper (§2) briefly reviews the history of the idea of the resonant nature of laminar-boundary-layer breakdown. In the second part a new wave-resonance concept of the breakdown mechanism is proposed. The existing experimental data on the laminar boundary layer (and plane channel flow) breakdown are analysed from the viewpoint of this concept and are compared with the well-known local high-frequency secondary-instability concept. The results testify to the correctness of the proposed wave-resonant concept for the initial stages of breakdown, in particular for the K-regime
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Ozdemir, Celalettin E., Tian-Jian Hsu, and S. Balachandar. "Direct numerical simulations of instability and boundary layer turbulence under a solitary wave." Journal of Fluid Mechanics 731 (August 28, 2013): 545–78. http://dx.doi.org/10.1017/jfm.2013.361.

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AbstractA significant amount of research effort has been made to understand the boundary layer instability and the generation and evolution of turbulence subject to periodic/oscillatory flows. However, little is known about bottom boundary layers driven by highly transient and intermittent free-stream flow forcing, such as solitary wave motion. To better understand the nature of the instability mechanisms and turbulent flow characteristics subject to solitary wave motion, a large number of direct numerical simulations are conducted. Different amplitudes of random initial fluctuating velocity f
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Bottaro, Alessandro, Inge L. Ryhming, Marc B. Wehrli, Franz S. Rys, and Paul Rys. "Laminar swirling flow and vortex breakdown in a pipe." Computer Methods in Applied Mechanics and Engineering 89, no. 1-3 (1991): 41–57. http://dx.doi.org/10.1016/0045-7825(91)90036-6.

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ZAKI, TAMER A., JAN G. WISSINK, WOLFGANG RODI, and PAUL A. DURBIN. "Direct numerical simulations of transition in a compressor cascade: the influence of free-stream turbulence." Journal of Fluid Mechanics 665 (October 27, 2010): 57–98. http://dx.doi.org/10.1017/s0022112010003873.

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The flow through a compressor passage without and with incoming free-stream grid turbulence is simulated. At moderate Reynolds number, laminar-to-turbulence transition can take place on both sides of the aerofoil, but proceeds in distinctly different manners. The direct numerical simulations (DNS) of this flow reveal the mechanics of breakdown to turbulence on both surfaces of the blade. The pressure surface boundary layer undergoes laminar separation in the absence of free-stream disturbances. When exposed to free-stream forcing, the boundary layer remains attached due to transition to turbul
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Jost, Dominic, and Kai Nagel. "Probabilistic Traffic Flow Breakdown in Stochastic Car-Following Models." Transportation Research Record: Journal of the Transportation Research Board 1852, no. 1 (2003): 152–58. http://dx.doi.org/10.3141/1852-19.

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Whether traffic displays multiple phases (e.g., laminar, jammed, synchronized) has been much discussed. Computational evidence is presented that a stochastic car-following model can be moved from two phases (laminar and jammed) to one phase by changing one of its parameters. Models with two phases show three states. Two of them are homogeneous and correspond to the two phases. The third state consists of a mix of the two phases (phase coexistence). Although the gas–liquid analogy to traffic models has been widely discussed, no traffic-related model ever displayed a completely understood stocha
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Sansica, Andrea, Neil D. Sandham, and Zhiwei Hu. "Instability and low-frequency unsteadiness in a shock-induced laminar separation bubble." Journal of Fluid Mechanics 798 (May 31, 2016): 5–26. http://dx.doi.org/10.1017/jfm.2016.297.

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Three-dimensional direct numerical simulations (DNS) of a shock-induced laminar separation bubble are carried out to investigate the flow instability and origin of any low-frequency unsteadiness. A laminar boundary layer interacting with an oblique shock wave at $M=1.5$ is forced at the inlet with a pair of monochromatic oblique unstable modes, selected according to local linear stability theory (LST) performed within the separation bubble. Linear stability analysis is applied to cases with marginal and large separation, and compared to DNS. While the parabolized stability equations approach a
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Dissertations / Theses on the topic "Laminar breakdown"

1

Brandt, Luca. "Study of generation, growth and breakdown of streamwise streaks in a Blasius boundary layer." Licentiate thesis, KTH, Mechanics, 2001. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-1256.

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<p>Transition from laminar to turbulent flow has beentraditionally studied in terms of exponentially growingeigensolutions to the linearized disturbance equations.However, experimental findings show that transition may occuralso for parameters combinations such that these eigensolutionsare damped. An alternative non-modal growth mechanism has beenrecently identified, also based on the linear approximation.This consists of the transient growth of streamwise elongateddisturbances, mainly in the streamwise velocity component,called streaks. If the streak amplitude reaches a thresholdvalue, second
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Silva, Guilherme Araújo Lima da. "Transferência de calor e massa no escoamento bifásico em torno de aerofólios equipados com sistemas de antigelo aeronáuticos." Universidade de São Paulo, 2009. http://www.teses.usp.br/teses/disponiveis/3/3150/tde-27032009-082825/.

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Há a necessidade de prevenir formação de gelo nas asas e nos estabilizadores de aeronaves, pois as formas de gelo podem causar a degradação do desempenho aerodinâmico, o aumento de peso, bem como dificuldades de controle e manobra que, em casos críticos, leva a uma diminuição da margem de segurança operacional. Quando as aeronaves atravessam nuvens com gotículas de água sub-resfriadas, ou seja, em equilíbrio metaestável, o crescimento de gelo ocorre nas superfícies não protegidas. Usualmente, os sistemas antigelo térmicos de aerofólios são projetados, desenvolvidos e certificados com o auxílio
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Sharma, Sushank. "Transition laminaire turbulent dans les couches limites supersoniques : différents scénarios et contrôle possible Control of oblique-type breakdown in a supersonic boundary layer employing streaks Turbulent flow topology in supersonic boundary layer with wall heat transfer Laminar-to-turbulent transition in supersonic boundary layer : : Effects of initial perturbation and wall heat transfer Effect of thermo-mechanical non-equilibrium on the onset of transition in supersonic boundary layers." Thesis, Normandie, 2019. http://www.theses.fr/2019NORMIR16.

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Les simulations numériques directes (DNS) des couches limites supersoniques adiabatiques et isothermes (chauffées et refroidies) sont effectuées. Deux différents scénarios de transition, à savoir la décomposition de type oblique et la transition de type 'by-pass', sont présentés en détail. Pour le scénario de transition de type oblique, les résultats montrent que les modes contrôles avec un nombre d'onde quatre à cinq fois supérieur au nombre fondamental se révèlent être bénéfiques pour contrôler la transition. Dans la première région après le forçage du mode de contrôle, la distorsion de flux
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Celep, Muhittin. "Τransitiοn dans les cοuches limites supersοniques : simulatiοns numériques directes et cοntrôle par stries". Electronic Thesis or Diss., Normandie, 2024. http://www.theses.fr/2024NORMIR15.

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Dans les écoulements à haute vitesse, une traînée visqueuse élevée et des charges thermiques importantes sont des conséquences inhérentes sur les corps aérodynamiques. Ces effets augmentent de manière significative pendant la phase de transition lorsque la couche limite devient turbulente. Afin de réduire les risques de dommages mécaniques et de défaillances liées à la fatigue, des systèmes de protection thermique sont intégrés aux véhicules, ajoutant de la complexité aux aspects techniques et économiques de la conception. La solution réside dans l’acquisition d’une compréhension approfondie d
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Gikas, Zacharias Z. "Effect of small pressure disturbances on the breakdown of round laminar and turbulent jets." Thesis, 1985. http://hdl.handle.net/10945/21295.

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Books on the topic "Laminar breakdown"

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Zang, Thomas A. Multiple paths to subharmonic laminar breakdown in a boundary layer. Institute for Computer Applications in Science and Engineering, 1989.

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2

Yousuff, Hussaini M., and Langley Research Center, eds. Multiple paths to subharmonic laminar breakdown in a boundary layer. National Aeronautics and Space Administration, Langley Research Center, 1990.

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3

United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., ed. Large-eddy simulation of laminar-turbulent breakdown at high speeds with dynamic subgrid-scale modeling. National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1993.

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United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., ed. Large-eddy simulation of laminar-turbulent breakdown at high speeds with dynamic subgrid-scale modeling. National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1993.

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United States. National Aeronautics and Space Administration. Scientific and Technical Information Program, ed. Large-eddy simulation of laminar-turbulent breakdown at high speeds with dynamic subgrid-scale modeling. National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1993.

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United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., ed. Large-eddy simulation of laminar-turbulent breakdown at high speeds with dynamic subgrid-scale modeling. National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1993.

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United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., ed. Large-eddy simulation of laminar-turbulent breakdown at high speeds with dynamic subgrid-scale modeling. National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1993.

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8

El-Hady, Nabil M. Large-eddy simulation of laminar-turbulent breakdown at high speeds with dynamic subgrid-scale modeling. Langley Research Center, 1993.

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United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., ed. Large-eddy simulation of laminar-turbulent breakdown at high speeds with dynamic subgrid-scale modeling. National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1993.

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Gikas, Zacharias Z. Effect of small pressure disturbances on the breakdown of round laminar and turbulent jets. 1985.

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Book chapters on the topic "Laminar breakdown"

1

Herbert, Thorwald, and Jeffrey D. Crouch. "Threshold Conditions for Breakdown of Laminar Boundary Layers." In Laminar-Turbulent Transition. Springer Berlin Heidelberg, 1990. http://dx.doi.org/10.1007/978-3-642-84103-3_7.

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2

Kachanov, Yury S. "Nonlinear Breakdown of Laminar Boundary Layer." In Nonlinear Instability of Nonparallel Flows. Springer Berlin Heidelberg, 1994. http://dx.doi.org/10.1007/978-3-642-85084-4_2.

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3

Tso, Jin, Shing-Ing Chang, and Ron F. Blackwelder. "On the Breakdown of a Wave Packet Disturbance in a Laminar Boundary Layer." In Laminar-Turbulent Transition. Springer Berlin Heidelberg, 1990. http://dx.doi.org/10.1007/978-3-642-84103-3_17.

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Kachanov, Yu S., V. V. Kozlov, V. Ya Levchenko, and M. P. Ramazanov. "On Nature of K-Breakdown of a Laminar Boundary Layer. New Experimental Data." In Laminar-Turbulent Transition. Springer Berlin Heidelberg, 1985. http://dx.doi.org/10.1007/978-3-642-82462-3_7.

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Boiko, A. V., V. V. Kozlov, V. V. Syzrantsev, and V. A. Scherbakov. "Experimental Study of Secondary Instability and Breakdown in a Swept Wing Boundary Layer." In Laminar-Turbulent Transition. Springer Berlin Heidelberg, 1995. http://dx.doi.org/10.1007/978-3-642-79765-1_34.

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Matsubara, M., A. A. Bakchinov, J. H. M. Fransson, and P. H. Alfredsson. "Growth and breakdown of streaky structures in boundary layer transition induced by free stream turbulence." In Laminar-Turbulent Transition. Springer Berlin Heidelberg, 2000. http://dx.doi.org/10.1007/978-3-662-03997-7_55.

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Kachanov, Y. S. "Secondary and Cascade Resonant Instabilities of Boundary Layers. Wave-Resonant Concept of a Breakdown and its Substantiation." In Laminar-Turbulent Transition. Springer Berlin Heidelberg, 1990. http://dx.doi.org/10.1007/978-3-642-84103-3_5.

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Asai, Masahito, Masayuki Minagawa, and Michio Nishioka. "Instability and Breakdown of the Three-Dimensional High-Shear Layer Associated with a Near-Wall Low-Speed Streak." In Laminar-Turbulent Transition. Springer Berlin Heidelberg, 2000. http://dx.doi.org/10.1007/978-3-662-03997-7_39.

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Zang, Thomas A. "Aspects of Laminar Breakdown in Boundary-Layer Transition." In Instability, Transition, and Turbulence. Springer New York, 1992. http://dx.doi.org/10.1007/978-1-4612-2956-8_37.

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Ji-sheng, Luo, Wang Xin-jun, and Zhou Heng. "INHERENT MECHANISM OF BREAKDOWN IN LAMINAR-TURBULENT TRANSITION." In Fluid Mechanics and Its Applications. Springer Netherlands, 2006. http://dx.doi.org/10.1007/1-4020-4159-4_36.

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Conference papers on the topic "Laminar breakdown"

1

Postlethwaite, J., B. Huber, and D. Makepeace. "Hydrodynamic Effects During Electrochemical and Exposure Pitting Tests with Passive Metals." In CORROSION 1986. NACE International, 1986. https://doi.org/10.5006/c1986-86273.

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Abstract Electrochemical pitting scans, dE/dt = 60 mV/h and 1,200 mV/h, and exposure tests have been done with nickel in an electrochemical flow cell to determine the effects of solution flow on the initiation, propagation and repassivation processes. The flat nickel specimens were exposed to 0.5 wt % NaCl solution in a rectangular duct, at Reynolds numbers in the range 420 to 19,600 and under stagnant conditions. There was no significant effect of flow on the value of the breakdown potential, Enp, in either the electrochemical tests or the exposure tests and it is concluded that the initiatio
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Ennis, Brandon, Christopher Kelley, and David Maniaci. "Dynamic Wake Meandering Model Comparison with Varying Fidelity Models for Wind Turbine Wake Prediction." In Vertical Flight Society 71st Annual Forum & Technology Display. The Vertical Flight Society, 2015. http://dx.doi.org/10.4050/f-0071-2015-10301.

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The dynamic wake meandering model (DWM) is a common wake model used for fast prediction of wind farm power and loads. This model is compared to higher fidelity vortex method (VM) and actuator line large eddy simulation (AL-LES) model results. By looking independently at the steady wake deficit model of DWM, and performing a more rigorous comparison than averaged result comparisons alone can produce, the models and their physical processes can be compared. The DWM and VM results of wake deficit agree best in the mid-wake region due to the consistent recovery prior to wake breakdown predicted in
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Hansen, Greg. "“Dollars & Cents - You Make the Choice: a Look at Elastomer Polyurethane versus Epoxy Laminate Lining Systems for the Linings of Water or Wastewater Structures”." In CONFERENCE 2022. AMPP, 2022. https://doi.org/10.5006/c2022-18202.

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Abstract The use of protective coatings is to enhance the durability of concrete structures by creating a barrier that will limit the penetration of water, acids, chemicals, solvents, and chlorides that will breakdown industrial or municipal infrastructure. Corrosion in concrete is not just caused by the constituents of wastewater, it can also be caused by the cleaning procedures of water treatment or membrane bioreactor (MBR) systems. Lining solution technologies presented included systems comprised of 100% solids epoxies, epoxy laminate alternatives and elastomer polyurethane applications. T
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STETSON, KENNETH, and ROGER KIMMEL. "On the breakdown of a hypersonic laminar boundary layer." In 31st Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics, 1993. http://dx.doi.org/10.2514/6.1993-896.

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PRUETT, C., and T. ZANG. "Direct numerical simulation of laminar breakdown in high-speed, axisymmetric boundary layers." In 30th Aerospace Sciences Meeting and Exhibit. American Institute of Aeronautics and Astronautics, 1992. http://dx.doi.org/10.2514/6.1992-742.

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Adams, N., and L. Kleiser. "Numerical simulation of fundamental breakdown of a laminar boundary-layer at Mach 4.5." In 5th International Aerospace Planes and Hypersonics Technologies Conference. American Institute of Aeronautics and Astronautics, 1993. http://dx.doi.org/10.2514/6.1993-5027.

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Watmuff, Jonathan H. "Effects of Weak Free Stream Nonuniformity on Boundary Layer Transition (Keynote Paper)." In ASME/JSME 2003 4th Joint Fluids Summer Engineering Conference. ASMEDC, 2003. http://dx.doi.org/10.1115/fedsm2003-45685.

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Experiments are described in which well-defined FSN (Free Stream Nonuniformity) distributions are introduced by placing fine wires upstream of the leading edge of a flat plate. Large amplitude spanwise thickness variations are present in the downstream boundary layer resulting from the interaction of the laminar wakes with the leading edge. Regions of elevated background unsteadiness appear on either side of the peak layer thickness, which share many of the characteristics of Klebanoff modes, observed at elevated Free Stream Turbulence (FST) levels. However, for the low background disturbance
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Kro¨ner, Martin, Jassin Fritz, and Thomas Sattelmayer. "Flashback Limits for Combustion Induced Vortex Breakdown in a Swirl Burner." In ASME Turbo Expo 2002: Power for Land, Sea, and Air. ASMEDC, 2002. http://dx.doi.org/10.1115/gt2002-30075.

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Flame flashback from the combustion chamber into the mixing zone limits the reliability of swirl stabilized lean premixed combustion in gas turbines. In a former study, the combustion induced vortex breakdown (CIVB) has been identified as a prevailing flashback mechanism of swirl burners. The present study has been performed to determine the flash-back limits of a swirl burner with cylindrical premixing tube without centerbody at atmospheric conditions. The flashback limits, herein defined as the upstream flame propagation through the entire mixing tube, have been detected by a special optical
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Watmuff, Jonathan H. "Sinuous Streak Instability and Breakdown in a Blasius Boundary Layer." In ASME 2010 3rd Joint US-European Fluids Engineering Summer Meeting collocated with 8th International Conference on Nanochannels, Microchannels, and Minichannels. ASMEDC, 2010. http://dx.doi.org/10.1115/fedsm-icnmm2010-31322.

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A narrow low-speed streamwise streak is deliberately introduced into an otherwise extremely spanwise uniform Blasius boundary layer. The streak shares many of the characteristics of Klebanoff modes known to be responsible for bypass transition at moderate Free Stream Turbulence (FST) levels. However, for the low background disturbance level of the free stream (u/U1 &amp;lt; 0.05%), the layer remains laminar to the end of the test section (Rx = 1.4 × 106) and there is no evidence of bursting or other phenomena associated with breakdown to turbulence. A harmonic disturbance is used to excite a s
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Ikeda, Yuji, Atsushi Nishiyama, Nobuyuki Kawahara, Eiji Tomita, and Takashi Nakayama. "Local equivalence ratio measurement of CH4/Air and C3H8/air laminar flames by laser-induced breakdown spectroscopy." In 44th AIAA Aerospace Sciences Meeting and Exhibit. American Institute of Aeronautics and Astronautics, 2006. http://dx.doi.org/10.2514/6.2006-965.

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Reports on the topic "Laminar breakdown"

1

Nayfeh, Ali H. Laminar Boundary-Layer Breakdown. Defense Technical Information Center, 1992. http://dx.doi.org/10.21236/ada254489.

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Glezer, A., Y. Katz, and I. Wygnanski. On the Breakdown of the Wave Packet Trailing a Turbulent Spot in a Laminar Layer. Defense Technical Information Center, 1986. http://dx.doi.org/10.21236/ada179607.

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