Auswahl der wissenschaftlichen Literatur zum Thema „Laminar breakdown“
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Zeitschriftenartikel zum Thema "Laminar breakdown"
Li, Ning, und Qi Hong Zeng. „Direct Numerical Simulation on Transition of an Incompressible Boundary Layer on a Flat Plate“. Applied Mechanics and Materials 268-270 (Dezember 2012): 1143–47. http://dx.doi.org/10.4028/www.scientific.net/amm.268-270.1143.
Der volle Inhalt der QuelleKadyirov, A. I., und 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.
Der volle Inhalt der QuelleZhou, Teng, Zaijie Liu, Yuhan Lu, Ying Wang und 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, Nr. 7 (Juli 2022): 074101. http://dx.doi.org/10.1063/5.0094069.
Der volle Inhalt der QuelleSeifi, Zeinab, Mehrdad Raisee und Michel J. Cervantes. „Optimal flow control of vortex breakdown in a laminar swirling flow“. Journal of Physics: Conference Series 2707, Nr. 1 (01.02.2024): 012129. http://dx.doi.org/10.1088/1742-6596/2707/1/012129.
Der volle Inhalt der QuelleKachanov, 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.
Der volle Inhalt der QuelleBottaro, Alessandro, Inge L. Ryhming, Marc B. Wehrli, Franz S. Rys und Paul Rys. „Laminar swirling flow and vortex breakdown in a pipe“. Computer Methods in Applied Mechanics and Engineering 89, Nr. 1-3 (August 1991): 41–57. http://dx.doi.org/10.1016/0045-7825(91)90036-6.
Der volle Inhalt der QuelleOzdemir, Celalettin E., Tian-Jian Hsu und S. Balachandar. „Direct numerical simulations of instability and boundary layer turbulence under a solitary wave“. Journal of Fluid Mechanics 731 (28.08.2013): 545–78. http://dx.doi.org/10.1017/jfm.2013.361.
Der volle Inhalt der QuelleZAKI, TAMER A., JAN G. WISSINK, WOLFGANG RODI und PAUL A. DURBIN. „Direct numerical simulations of transition in a compressor cascade: the influence of free-stream turbulence“. Journal of Fluid Mechanics 665 (27.10.2010): 57–98. http://dx.doi.org/10.1017/s0022112010003873.
Der volle Inhalt der QuelleJost, Dominic, und Kai Nagel. „Probabilistic Traffic Flow Breakdown in Stochastic Car-Following Models“. Transportation Research Record: Journal of the Transportation Research Board 1852, Nr. 1 (Januar 2003): 152–58. http://dx.doi.org/10.3141/1852-19.
Der volle Inhalt der QuelleZang, Thomas A., und M. Yousuff Hussaini. „Multiple paths to subharmonic laminar breakdown in a boundary layer“. Physical Review Letters 64, Nr. 6 (05.02.1990): 641–44. http://dx.doi.org/10.1103/physrevlett.64.641.
Der volle Inhalt der QuelleDissertationen zum Thema "Laminar breakdown"
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.
Der volle Inhalt der QuelleTransition 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, secondary instabilities can take place and provoketransition. This scenario is most likely to occur in boundarylayer flows subject to high levels of free-stream turbulenceand is the object of this thesis. Different stages of theprocess are isolated and studied with different approaches,considering the boundary layer flow over a flat plate. Thereceptivity to free-stream disturbances has been studiedthrough a weakly non-linear model which allows to disentanglethe features involved in the generation of streaks. It is shownthat the non-linear interaction of oblique waves in thefree-stream is able to induce strong streamwise vortices insidethe boundary layer, which, in turn, generate streaks by thelift-up effect. The growth of steady streaks is followed bymeans of Direct Numerical Simulation. After the streaks havereached a finite amplitude, they saturate and a new laminarflow, characterized by a strong spanwise modulation isestablished. Using Floquet theory, the instability of thesestreaks is studied to determine the features of theirbreakdown. The streak critical amplitude, beyond which unstablewaves are excited, is 26% of the free-stream velocity. Theinstability appears as spanwise (sinuous-type) oscillations ofthe streak. The late stages of the transition, originating fromthis type of secondary instability, are also studied. We foundthat the main structures observed during the transition processconsist of elongated quasi-streamwise vortices located on theflanks of the low speed streak. Vortices of alternating signare overlapping in the streamwise direction in a staggeredpattern.
Descriptors:Fluid mechanics, laminar-turbulenttransition, boundary layer flow, transient growth, streamwisestreaks, lift-up effect, receptivity, free-stream turbulence,nonlinear mechanism, streak instability, secondary instability,Direct Numerical Simulation.
QC 20100518
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/.
Der volle Inhalt der QuelleIt is required to prevent ice accretion on wings and horizontal stabilizers because it may cause aerodynamic performance degradation, weight increase, flight control difficulties and, in critical cases, may lead to operational safety margins reduction. When aircraft flies through clouds containnig supercooled water droplets, which are in metastable equilibrium, ice will form in all non-protected surfaces. Usually, anti-ice protection systems are designed, developed and certified with a support from a numerical tool. The present describes the development and implementation of a mathematical model for prediction of heat and mass transfer in two-phase flow around airfoils, which are equipped with thermal anti-ice system and operating in steady state regime. Under icing conditions, it is necessary to heat and control the temperature of the airfoil surface at leading edge region to prevent ice formation. The heating system balances the evaporative cooling effects, which are caused by the coupled heat and mass convection transfer, imposed by the air flow loaded with supercooled water droplets and the runback water flow around the airfoil. The present work implemented submodels to: 1) estimate airfoil surface wetness factor by adopting a liquid water film flow model as well as a rivulet formation and flow model; 2) evaluate laminar and turbulent boundary layers with pressure gradient and laminar-turbulent transition over nonisothermal and permeable airfoil surface by implementing differential boundary layer analysis and 3) predict the onset position and length of laminar-turbulent transition region. The present paper followed a validation and verification process during the numerical code development. All sub-models results were verified separately against experimental data before their inclusion in anti-ice model.The results of anti-ice model with selected submodels were validated against reference cases. The results were considered suficiently accurate when solving the film breakdown and rivulets formation by total mechanical energy method, compressible boundary layer by differential analysis and laminar-turbulent transition prediction by algebraic correlations, which considered pressure gradient and freestream turbulence level.
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.
Der volle Inhalt der QuelleDirect numerical simulations (DNS) of both adiabatic and isothermal (heated and cooled) supersonic boundary layers are performed. Two different transition scenarios, namely the Oblique-type breakdown and the By-pass transition are presented in detail. For the oblique-type transition scenario, the results show that the control modes with four to five times the fundamental wavenumber are beneficial for controlling the transition. In the first region, after the control-mode forcing, the beneficial mean-flow distortion (MFD) generated by inducing the control mode is solely responsible for hampering the growth of the fundamental-mode. Globally, the MFD and the three-dimensional part of the control contribute equally towards controlling the oblique breakdown. Effects of physical parameters like wall-temperature, perturbation intensity and baseflow are investigated for the By-pass transition. The results regarding the by-pass scenario reveal that increasing the perturbation intensity moves the transition onset upstream and also increases the length of the transition region. Additionally, below 1% perturbation levels, wall-cooling stabilizes the flow while inverse happens at higher values. The existence of the thermo-mechanical non-equilibrium advances the onset of transition for the heated cases while the cooled wall behaves in the opposite sense. The analyses of the turbulent boundary layer show that the thermal factors influence the topology and inclination of the vortical structures. Moreover, regarding the heat flux, different transfer process is dominant in the near-wall region for the cooled wall
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.
Der volle Inhalt der QuelleIn high-speed flows, elevated viscous drag and thermal loads are inherent outcomes over aerodynamic bodies. These effects escalate substantially during the transition phase when the boundary layer becomes turbulent. To mitigate potential mechanical damage and fatigue-related failures, thermal protection systems are integrated into vehicles, adding complexity to the technical and economic aspects of design. The solution lies in gaining a comprehensive understanding of transition mechanisms and developing control systems to prolong laminar boundary layer along the vehicle’s surface. Numerous active and passive control techniques can be employed for transition control, with the streak employment method emerging as a particularly promising approach. This method involves generating narrowly spaced streaks in the spanwise direction, creating alternating high and low-speed regions in the flow field. Although the method has only recently been tested in supersonic flows, demonstrating its effectiveness in delaying transition, its suitability needs to be assessed further. In this research work, direct numerical simulations are performed in supersonic and near-hypersonic regimes. Streaks are introduced through a blowing/suction strip placed at the wall prior to that of the perturbation which is used to trigger transition in a “controlled” fashion, forced by a single frequency and wavenumber disturbance. The investigation at Mach 2.0 confirms that streaks with five times the fundamental wavenumber are most beneficial for transition control. Additionally, cooling enhances the method’s effectiveness, while heating severely deteriorates the capability of control streaks. The isothermal wall condition does not alter the comparable stabilizing impact of the mean flow deformation (MFD) and the 3-D part of the control at Mach 2.0. However, at Mach 4.5, both the type of instability and the characteristics of the streaks change significantly. The stabilizing impact of the MFD becomes nearly absent, and the 3-D part of the control predominates, with the characteristics of the streaks no longer considered independent of their initial disturbance amplitude
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.
Der volle Inhalt der QuelleBücher zum Thema "Laminar breakdown"
Zang, Thomas A. Multiple paths to subharmonic laminar breakdown in a boundary layer. Hampton, Va: Institute for Computer Applications in Science and Engineering, 1989.
Den vollen Inhalt der Quelle findenYousuff, Hussaini M., und Langley Research Center, Hrsg. Multiple paths to subharmonic laminar breakdown in a boundary layer. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1990.
Den vollen Inhalt der Quelle findenUnited States. National Aeronautics and Space Administration. Scientific and Technical Information Program., Hrsg. Large-eddy simulation of laminar-turbulent breakdown at high speeds with dynamic subgrid-scale modeling. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1993.
Den vollen Inhalt der Quelle findenUnited States. National Aeronautics and Space Administration. Scientific and Technical Information Program., Hrsg. Large-eddy simulation of laminar-turbulent breakdown at high speeds with dynamic subgrid-scale modeling. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1993.
Den vollen Inhalt der Quelle findenUnited States. National Aeronautics and Space Administration. Scientific and Technical Information Program, Hrsg. Large-eddy simulation of laminar-turbulent breakdown at high speeds with dynamic subgrid-scale modeling. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1993.
Den vollen Inhalt der Quelle findenUnited States. National Aeronautics and Space Administration. Scientific and Technical Information Program., Hrsg. Large-eddy simulation of laminar-turbulent breakdown at high speeds with dynamic subgrid-scale modeling. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1993.
Den vollen Inhalt der Quelle findenUnited States. National Aeronautics and Space Administration. Scientific and Technical Information Program., Hrsg. Large-eddy simulation of laminar-turbulent breakdown at high speeds with dynamic subgrid-scale modeling. [Washington, D.C.]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1993.
Den vollen Inhalt der Quelle findenEl-Hady, Nabil M. Large-eddy simulation of laminar-turbulent breakdown at high speeds with dynamic subgrid-scale modeling. Hampton, Va: Langley Research Center, 1993.
Den vollen Inhalt der Quelle findenUnited States. National Aeronautics and Space Administration. Scientific and Technical Information Program., Hrsg. Large-eddy simulation of laminar-turbulent breakdown at high speeds with dynamic subgrid-scale modeling. [Washington, D.C.]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1993.
Den vollen Inhalt der Quelle findenGikas, Zacharias Z. Effect of small pressure disturbances on the breakdown of round laminar and turbulent jets. 1985.
Den vollen Inhalt der Quelle findenBuchteile zum Thema "Laminar breakdown"
Herbert, Thorwald, und Jeffrey D. Crouch. „Threshold Conditions for Breakdown of Laminar Boundary Layers“. In Laminar-Turbulent Transition, 93–101. Berlin, Heidelberg: Springer Berlin Heidelberg, 1990. http://dx.doi.org/10.1007/978-3-642-84103-3_7.
Der volle Inhalt der QuelleKachanov, Yury S. „Nonlinear Breakdown of Laminar Boundary Layer“. In Nonlinear Instability of Nonparallel Flows, 21–51. Berlin, Heidelberg: Springer Berlin Heidelberg, 1994. http://dx.doi.org/10.1007/978-3-642-85084-4_2.
Der volle Inhalt der QuelleTso, Jin, Shing-Ing Chang und Ron F. Blackwelder. „On the Breakdown of a Wave Packet Disturbance in a Laminar Boundary Layer“. In Laminar-Turbulent Transition, 199–214. Berlin, Heidelberg: Springer Berlin Heidelberg, 1990. http://dx.doi.org/10.1007/978-3-642-84103-3_17.
Der volle Inhalt der QuelleKachanov, Yu S., V. V. Kozlov, V. Ya Levchenko und M. P. Ramazanov. „On Nature of K-Breakdown of a Laminar Boundary Layer. New Experimental Data“. In Laminar-Turbulent Transition, 61–73. Berlin, Heidelberg: Springer Berlin Heidelberg, 1985. http://dx.doi.org/10.1007/978-3-642-82462-3_7.
Der volle Inhalt der QuelleBoiko, A. V., V. V. Kozlov, V. V. Syzrantsev und V. A. Scherbakov. „Experimental Study of Secondary Instability and Breakdown in a Swept Wing Boundary Layer“. In Laminar-Turbulent Transition, 289–95. Berlin, Heidelberg: Springer Berlin Heidelberg, 1995. http://dx.doi.org/10.1007/978-3-642-79765-1_34.
Der volle Inhalt der QuelleMatsubara, M., A. A. Bakchinov, J. H. M. Fransson und P. H. Alfredsson. „Growth and breakdown of streaky structures in boundary layer transition induced by free stream turbulence“. In Laminar-Turbulent Transition, 371–76. Berlin, Heidelberg: Springer Berlin Heidelberg, 2000. http://dx.doi.org/10.1007/978-3-662-03997-7_55.
Der volle Inhalt der QuelleKachanov, Y. S. „Secondary and Cascade Resonant Instabilities of Boundary Layers. Wave-Resonant Concept of a Breakdown and its Substantiation“. In Laminar-Turbulent Transition, 65–80. Berlin, Heidelberg: Springer Berlin Heidelberg, 1990. http://dx.doi.org/10.1007/978-3-642-84103-3_5.
Der volle Inhalt der QuelleAsai, Masahito, Masayuki Minagawa und Michio Nishioka. „Instability and Breakdown of the Three-Dimensional High-Shear Layer Associated with a Near-Wall Low-Speed Streak“. In Laminar-Turbulent Transition, 269–74. Berlin, Heidelberg: Springer Berlin Heidelberg, 2000. http://dx.doi.org/10.1007/978-3-662-03997-7_39.
Der volle Inhalt der QuelleZang, Thomas A. „Aspects of Laminar Breakdown in Boundary-Layer Transition“. In Instability, Transition, and Turbulence, 377–87. New York, NY: Springer New York, 1992. http://dx.doi.org/10.1007/978-1-4612-2956-8_37.
Der volle Inhalt der QuelleJi-sheng, Luo, Wang Xin-jun und Zhou Heng. „INHERENT MECHANISM OF BREAKDOWN IN LAMINAR-TURBULENT TRANSITION.“ In Fluid Mechanics and Its Applications, 267–73. Dordrecht: Springer Netherlands, 2006. http://dx.doi.org/10.1007/1-4020-4159-4_36.
Der volle Inhalt der QuelleKonferenzberichte zum Thema "Laminar breakdown"
STETSON, KENNETH, und ROGER KIMMEL. „On the breakdown of a hypersonic laminar boundary layer“. In 31st Aerospace Sciences Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1993. http://dx.doi.org/10.2514/6.1993-896.
Der volle Inhalt der QuellePRUETT, C., und T. ZANG. „Direct numerical simulation of laminar breakdown in high-speed, axisymmetric boundary layers“. In 30th Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1992. http://dx.doi.org/10.2514/6.1992-742.
Der volle Inhalt der QuelleAdams, N., und 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. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1993. http://dx.doi.org/10.2514/6.1993-5027.
Der volle Inhalt der QuelleWatmuff, 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.
Der volle Inhalt der QuelleIkeda, Yuji, Atsushi Nishiyama, Nobuyuki Kawahara, Eiji Tomita und 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. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2006. http://dx.doi.org/10.2514/6.2006-965.
Der volle Inhalt der QuelleEaves, L. „Quantum Hall Effect Breakdown Steps due to an Instability of Laminar Flow against Electron-Hole Pair Formation“. In Proceedings of Nobel Symposium 116. WORLD SCIENTIFIC, 2001. http://dx.doi.org/10.1142/9789812811004_0029.
Der volle Inhalt der QuelleKro¨ner, Martin, Jassin Fritz und 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.
Der volle Inhalt der QuelleWatmuff, 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.
Der volle Inhalt der QuelleSchmidt, Jacob, und Biswa Ganguly. „Transition from stable laminar to highly unstable behavior in premixed propane/air flame with sub-breakdown electric field“. In 50th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2012. http://dx.doi.org/10.2514/6.2012-377.
Der volle Inhalt der QuelleAbraham, J. P., E. M. Sparrow, J. C. K. Tong und W. J. Minkowycz. „Intermittent Flow Modeling: Part I—Hydrodynamic and Thermal Modeling of Steady, Intermittent Flows in Constant Area Ducts“. In 2010 14th International Heat Transfer Conference. ASMEDC, 2010. http://dx.doi.org/10.1115/ihtc14-22858.
Der volle Inhalt der QuelleBerichte der Organisationen zum Thema "Laminar breakdown"
Nayfeh, Ali H. Laminar Boundary-Layer Breakdown. Fort Belvoir, VA: Defense Technical Information Center, Juli 1992. http://dx.doi.org/10.21236/ada254489.
Der volle Inhalt der QuelleGlezer, A., Y. Katz und I. Wygnanski. On the Breakdown of the Wave Packet Trailing a Turbulent Spot in a Laminar Layer. Fort Belvoir, VA: Defense Technical Information Center, Januar 1986. http://dx.doi.org/10.21236/ada179607.
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