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Добірка наукової літератури з теми "Laminar layer"

Автор: Grafiati
Опубліковано: 11 березня 2023

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Статті в журналах з теми "Laminar layer"

1

Forster, E., C. Kaltschmidt, J. Deng, H. Cremer, T. Deller, and M. Frotscher. "Lamina-specific cell adhesion on living slices of hippocampus." Development 125, no. 17 (September 1, 1998): 3399–410. http://dx.doi.org/10.1242/dev.125.17.3399.

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Laminar distribution of fiber systems is a characteristic feature of hippocampal organization. Ingrowing afferents, e.g. the fibers from the entorhinal cortex, terminate in specific layers, which implies the existence of laminar recognition cues. To identify cues that are involved in the laminar segregation of fiber systems in the hippocampus, we used an in vitro assay to study the adhesion of dissociated entorhinal cells on living hippocampal slices. Here we demonstrate that dissociated entorhinal cells adhere to living hippocampal slices with a lamina-specific distribution that reflects the innervation pattern of the entorhino-hippocampal projection. In contrast, laminae which are not invaded by entorhinal fibers are a poor substrate for cell adhesion. Lamina-specific cell adhesion does not require the neural cell adhesion molecule or the extracellular matrix glycoprotein reelin, as revealed in studies with mutants. However, the pattern of adhesive cues in the reeler mouse hippocampus mimics characteristic alterations of the entorhinal projection in this mutant, suggesting a role of layer-specific adhesive cues in the pathfinding of entorhinal fibers. Lamina-specific cell adhesion is independent of divalent cations, is abolished after cryofixation or paraformaldehyde fixation and is recognized across species. By using a novel membrane adhesion assay, we show that lamina-specific cell adhesion can be mimicked by membrane-coated fluorescent microspheres. Recognition of the adhesive properties of different hippocampal laminae by growing axons, as either a growth permissive or a non-permissive substrate, may provide a developmental mechanism underlying the segregation of lamina-specific fiber projections.
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2

Giepman, R. H. M., F. F. J. Schrijer, and B. W. van Oudheusden. "A parametric study of laminar and transitional oblique shock wave reflections." Journal of Fluid Mechanics 844 (April 4, 2018): 187–215. http://dx.doi.org/10.1017/jfm.2018.165.

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High-resolution particle image velocimetry measurements were performed on laminar and transitional oblique shock wave reflections for a range of Mach numbers ($M=1.6{-}2.3$), Reynolds numbers ($Re_{x_{sh}}=1.4\times 10^{6}{-}3.5\times 10^{6}$) and flow deflection angles ($\unicode[STIX]{x1D703}=1^{\circ }{-}5^{\circ }$ or $p_{3}/p_{1}=1.11{-}1.64$). The laminar interactions revealed a long, flat and triangular shaped separation bubble. For relatively strong interactions ($p_{3}/p_{1}>1.2$), the bubble grows linearly in the upstream direction with increasing shock strength. Under these conditions, the boundary layer keeps an on average laminar velocity profile up to the shock impingement location, followed by a quick transition and subsequent reattachment of the boundary layer. For weaker interactions ($p_{3}/p_{1}<1.2$), the boundary layer is able to remain laminar further downstream of the bubble, which consequently results in a later reattachment of the boundary layer. The pressure distribution at the interaction onset for all laminar cases shows excellent agreement with the free-interaction theory, therefore supporting its validity even for incipiently separated laminar oblique shock wave reflections.
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3

Atencio, Craig A., and Christoph E. Schreiner. "Laminar Diversity of Dynamic Sound Processing in Cat Primary Auditory Cortex." Journal of Neurophysiology 103, no. 1 (January 2010): 192–205. http://dx.doi.org/10.1152/jn.00624.2009.

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For primary auditory cortex (AI) laminae, there is little evidence of functional specificity despite clearly expressed cellular and connectional differences. Natural sounds are dominated by dynamic temporal and spectral modulations and we used these properties to evaluate local functional differences or constancies across laminae. To examine the layer-specific processing of acoustic modulation information, we simultaneously recorded from multiple AI laminae in the anesthetized cat. Neurons were challenged with dynamic moving ripple stimuli and we subsequently computed spectrotemporal receptive fields (STRFs). From the STRFs, temporal and spectral modulation transfer functions (tMTFs, sMTFs) were calculated and compared across layers. Temporal and spectral modulation properties often differed between layers. On average, layer II/III and VI neurons responded to lower temporal modulations than those in layer IV. tMTFs were mainly band-pass in granular layer IV and became more low-pass in infragranular layers. Compared with layer IV, spectral MTFs were broader and their upper cutoff frequencies higher in layers V and VI. In individual penetrations, temporal modulation preference was similar across layers for roughly 70% of the penetrations, suggesting a common, columnar functional characteristic. By contrast, only about 30% of penetrations showed consistent spectral modulation preferences across layers, indicative of functional laminar diversity or specialization. Since local laminar differences in stimulus preference do not always parallel the main flow of information in the columnar cortical microcircuit, this indicates the influence of additional horizontal or thalamocortical inputs. AI layers that express differing modulation properties may serve distinct roles in the extraction of dynamic sound information, with the differing information specific to the targeted stations of each layer.
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4

Djenidi, L., F. Anselmet, J. Liandrat, and L. Fulachier. "Laminar boundary layer over riblets." Physics of Fluids 6, no. 9 (September 1994): 2993–99. http://dx.doi.org/10.1063/1.868429.

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5

Anderson, E. J., W. R. McGillis, and M. A. Grosenbaugh. "The boundary layer of swimming fish." Journal of Experimental Biology 204, no. 1 (January 1, 2001): 81–102. http://dx.doi.org/10.1242/jeb.204.1.81.

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Tangential and normal velocity profiles of the boundary layer surrounding live swimming fish were determined by digital particle tracking velocimetry, DPTV. Two species were examined: the scup Stenotomus chrysops, a carangiform swimmer, and the smooth dogfish Mustelus canis, an anguilliform swimmer. Measurements were taken at several locations over the surfaces of the fish and throughout complete undulatory cycles of their propulsive motions. The Reynolds number based on length, Re, ranged from 3×10(3) to 3×10(5). In general, boundary layer profiles were found to match known laminar and turbulent profiles including those of Blasius, Falkner and Skan and the law of the wall. In still water, boundary layer profile shape always suggested laminar flow. In flowing water, boundary layer profile shape suggested laminar flow at lower Reynolds numbers and turbulent flow at the highest Reynolds numbers. In some cases, oscillation between laminar and turbulent profile shapes with body phase was observed. Local friction coefficients, boundary layer thickness and fluid velocities at the edge of the boundary layer were suggestive of local oscillatory and mean streamwise acceleration of the boundary layer. The behavior of these variables differed significantly in the boundary layer over a rigid fish. Total skin friction was determined. Swimming fish were found to experience greater friction drag than the same fish stretched straight in the flow. Nevertheless, the power necessary to overcome friction drag was determined to be within previous experimentally measured power outputs. No separation of the boundary layer was observed around swimming fish, suggesting negligible form drag. Inflected boundary layers, suggestive of incipient separation, were observed sporadically, but appeared to be stabilized at later phases of the undulatory cycle. These phenomena may be evidence of hydrodynamic sensing and response towards the optimization of swimming performance.
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6

Zhang, Jiaojiao, Shengna Liu, and Liancun Zheng. "Turbulent boundary layer heat transfer of CuO–water nanofluids on a continuously moving plate subject to convective boundary." Zeitschrift für Naturforschung A 77, no. 4 (December 21, 2021): 369–77. http://dx.doi.org/10.1515/zna-2021-0268.

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Abstract The turbulent boundary layer (TBL) heat transfer of CuO–water nanofluids on a continuously moving plate subject to convective boundary are investigated. Five different shapes of nanoparticles are taken into account. Prandtl mixing length theory is adopted to divide the TBL into two parts, laminar sub-layer and turbulent region. The numerical solutions are obtained by bvp4c and accuracy is verified with previous results. It is found that the transfer of momentum and heat in the TBL is more obvious in laminar sub-layer than in turbulent region. The rise of velocity ratio parameter increases the velocity and temperature while decreases the local friction coefficient. The heat transfer increases significantly with the increase of velocity ratio parameter, Biot number, and nanoparticles volume fraction. For nanoparticles of different shapes, the heat transfer characteristics are Nu x (sphere) < Nu x (hexahedron) < Nu x (tetrahedron) < Nu x (column) < Nu x (lamina).
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7

Raić, Karlo. "Simplification of laminar boundary layer equations." Metallurgical and Materials Engineering 24, no. 2 (July 2, 2018): 93–102. http://dx.doi.org/10.30544/347.

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The laminar boundary layer theory has been involved in two domains of transport phenomena: (i) steady-state flow (via Blasius eq.) and (ii) unsteady state flow and/or nonflow (via Newton, Fourier and/or Fick’s equations). Listed partial differential equations with the similarity of solutions enable the substitution of the observed phenomena by only one-second order differential equation. Consequently, an approach established on the general polynomial solution is described. Numerical verification of the concept is presented. Experimental notifications are documented. Finally, the new simulation strategy is suggested.
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8

Alston, Thomas M., and Ira M. Cohen. "Decay of a laminar shear layer." Physics of Fluids A: Fluid Dynamics 4, no. 12 (December 1992): 2690–99. http://dx.doi.org/10.1063/1.858456.

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9

Qiu, Jinhao, Junji Tani, Toshiyuki Hayase, and Takashi Okutani. "Active control of laminar boundary layer." Matériaux & Techniques 90 (2002): 13–17. http://dx.doi.org/10.1051/mattech/200290120013s.

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10

Kuz’min, A. I., and S. S. Kharchenko. "Self ignition in laminar mixing layer." Combustion, Explosion, and Shock Waves 35, no. 1 (January 1999): 23–30. http://dx.doi.org/10.1007/bf02674382.

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Дисертації з теми "Laminar layer"

1

Bown, Nicholas William. "In-flight boundary layer studies on laminar flow nacelles." Thesis, University of Oxford, 1995. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.299777.

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2

Choudhari, Meelan. "Boundary layer receptivity mechanisms relevant to laminar flow control." Diss., The University of Arizona, 1990. http://hdl.handle.net/10150/184964.

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Receptivity processes by which free-stream acoustic waves generate instability waves in boundary layers are investigated. Concentration is placed on mechanisms associated with local regions of short scale variation in wall suction or admittance distribution. These mechanisms are relevant to laminar flow control technology, in which suction is utilized to control the growth of boundary layer instabilities. The receptivity process requires a transfer of energy from the long wavelength of the free-stream disturbance to the short wavelength of the instability wave. In the case of wall suction, this occurs through the unsteady modulation, by the acoustic wave, of the short scale mean flow variation due to the steady wall suction. In the wall admittance mechanism, the boundary condition for the unsteady motion contains a short scale variation which directly scatters energy from the acoustic wave into the instability wave. The latter mechanism does not require a short scale adjustment in the mean boundary layer. Time harmonic, two and three-dimensional interactions are analyzed using the asymptotic, high Reynolds number, triple deck structure. The influence of subsonic compressibility is examined for the case of two-dimensional interactions, and a similarity transform is found which reduces the problem to an equivalent incompressible flow. For three-dimensional interactions, a similarity transform is possible only in the Fourier transform wavenumber space, and in the equivalent two-dimensional problem the frequency is complex. However, in many cases of practical interest, the imaginary component of this frequency is quite small and can be neglected. The acoustic wave orientation and the geometry of the wall suction or admittance distribution are found to significantly influence the amplitude of the generated instability wave. For an isolated, three-dimensional region of wall suction or admittance, instability wave growth is confined to a downstream, wedge shaped region. The saddle point method is utilized to calculate the characteristics of this instability wave pattern. In some ranges of parameter space, two saddle points are found to make comparable contributions. The instability wave pattern in these directions exhibits a beat phenomenon, due to constructive and destructive interference of the contributions from the two saddle points.
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3

Mackerrell, O. S. "Some hydrodynamic instabilities of boundary layer flows." Thesis, University of Exeter, 1988. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.381355.

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4

Rogers, John B. "Numerical computations for laminar mixing layers between parallel supersonic streams." Thesis, Georgia Institute of Technology, 1991. http://hdl.handle.net/1853/16441.

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5

Choudhari, Meelan 1963. "Boundary layer receptivity at a suction surface-hard wall junction." Thesis, The University of Arizona, 1989. http://hdl.handle.net/10150/277030.

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Receptivity refers to the generation of boundary layer instability waves by external disturbances. Recent work by M. E. Goldstein has set the general framework for the different types of boundary layer receptivity mechanisms. Therefore, it is now understood that receptivity occurs near the leading edge or at locations downstream where the boundary layer undergoes a rapid streamwise adjustment. The present work analyzes the receptivity due to a free-stream acoustic wave interacting with a suction surface--hard wall junction. In this case, receptivity occurs because of the rapid changes in wall suction distribution. Analytical expressions for the amplitude of the generated instability wave have been derived and numerical estimates provided for parameter values typical of hybrid laminar flow control applications. The importance of the junction receptivity as compared to other receptivity mechanisms has been assessed.
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6

Fabbiane, Nicolò. "Adaptive and model-based control in laminar boundary-layer flows." Licentiate thesis, KTH, Mekanik, 2014. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-154052.

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In boundary-layer flows it is possible to reduce the friction drag by breaking the path from laminar to turbulent state. In low turbulence environments, the laminar-to-turbulent transition is dominated by local flow instabilities – Tollmien-Schlichting (TS) waves – that exponentially grows while being con- vected by the flow and, eventually, lead to transition. Hence, by attenuating these disturbances via localised forcing in the flow it is possible to delay farther downstream the onset of turbulence and reduce the friction drag. Reactive control techniques are widely investigated to this end. The aim of this work is to compare model-based and adaptive control techniques and show how the adaptivity is crucial to control TS-waves in real applications. The control design consists in (i) choosing sensors and actuators and (ii) designing the system responsible to process on-line the measurement signals in order to compute an appropriate forcing by the actuators. This system, called compen- sator, can be static or adaptive, depending on the possibility of self-adjusting its response to unmodelled flow dynamics. A Linear Quadratic Gaussian (LQG) regulator is chosen as representative of static controllers. Direct numerical simulations of the flow are performed to provide a model for the compensator design and test its performance. An adaptive Filtered-X Least-Mean-Squares (FXLMS) compensator is also designed for the same flow case and its per- formance is compared to the model-based compensator via simulations and experiments. Although the LQG regulator behaves better at design conditions, it lacks robustness to small flow variations. On the other hand, the FXLMS compensator proved to be able to adapt its response to overcome the varied conditions and perform an adequate control action. It is thus found that an adaptive control technique is more suitable to delay the laminar-to-turbulent transition in situations where an accurate model of the flow is not available.
I det tunna gränsskikt som uppstår en yta, kan friktionen minskas genom att förhindra omslag från ett laminärt till ett turbulent flöde. När turbulensnivån är låg  i omgivningen, domineras till en början omslaget av lokala instabiliteter (Tollmien-Schlichting (TS) v ågor) som växer i en exponentiell takt samtidigt som de propagerar nedströms. Därför, kan man förskjuta omslaget genom att dämpa TS vågors tillväxt i ett gränsskikt och därmed minska friktionen.Med detta mål i sikte, tillämpas och jämförs två reglertekniska metoder, nämligen en adaptiv signalbaserad metod och en statiskt modellbaserad metod. Vi visar att adaptivitet är av avgörande betydelse för att kunna dämpa TS vågor i en verklig miljö. Den reglertekniska konstruktionen består av val av givare och aktuatorer samt att bestämma det system som behandlar mätsignaler (on- line) för beräkning av en lämplig signal till aktuatorer. Detta system, som kallas för en kompensator, kan vara antingen statisk eller adaptiv, beroende på om det har möjlighet till att anpassa sig till omgivningen. En så kallad linjär regulator (LQG), som representerar den statiska kompensator, har tagits fram med hjälp av numeriska simuleringar of strömningsfältet. Denna kompensator jämförs med en adaptiv regulator som kallas för Filtered-X Least-Mean-Squares (FXLMS) både experimentellt och numeriskt. Det visar sig att LQG regulatorn har en bättre prestanda än FXLMS för de parametrar som den var framtagen för, men brister i robusthet. FXLMS å andra sidan, anpassar sig till icke- modellerade störningar och variationer, och kan därmed hålla en god och jämn prestanda.Man kan därmed dra slutsaten att adaptiva regulatorer är mer lämpliga för att förhala omslaget fr ån laminär till turbulent strömning i situationer då en exakt modell av fysiken saknas.

QC 20141020

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Sattarzadeh, Shirvan Sohrab. "Boundary layer streaks as a novel laminar flow control method." Doctoral thesis, KTH, Stabilitet, Transition, Kontroll, 2016. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-181899.

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A novel laminar flow control based on generation of spanwise mean velocity gradients (SVG) in a flat plate boundary layer is investigated where disturbances of different types are introduced in the wall-bounded shear layer. The experimental investigations are aimed at; (i) generating stable and steady streamwise streaks in the boundary layer which set up spanwise gradients in the mean flow, and (ii) attenuating disturbance energy growth in the streaky boundary layers and hence delaying the onset of turbulence transition. The streamwise streaks generated by four different methods are investigated, which are spanwise arrays of triangular/rectangular miniature vortex generators (MVGs) and roughness elements, non-linear pair of oblique waves, and spanwise-periodic finite discrete suction. For all the investigated methods the boundary layer is modulated into regions of high- and low speed streaks through formation of pairs of counter-rotating streamwise vortices. For the streaky boundary layers generated by the MVGs a parameter study on a wide range of MVG configurations is performed in order to investigate the transient growth of the streaks. A general scaling of the streak amplitudes is found based on empiricism where an integral amplitude definition is proposed for the streaks. The disturbances are introduced as single- and broad band frequency twodimensional Tollmien–Schlichting (TS) waves, and three-dimensional single and a pair of oblique waves. In an attempt to obtain a more realistic configuration compared to previous investigations the disturbances are introduced upstream of the location were streaks are generated. It is shown that the SVG method is efficient in attenuating the growth of disturbance amplitudes in the linear regime for a wide range of frequencies although the disturbances have an initial amplitude response to the generation of the streaks. The attenuation rate of the disturbance amplitude is found to be optimized for an integral streak amplitude of 30% of the free-stream velocity which takes into account the periodic wavelength of the streaky base flow. The stabilizing effect of the streamwise streaks can be extended to the nonlinear regime of disturbances which in turn results in transition to turbulence delay. This results in significant drag reduction when comparing the skin friction coefficient of a laminar- to a turbulent boundary layer. It is also shown that consecutive turbulence transition delay can be obtained by reinforcing the streaky boundary layer in the streamwise direction. For the streaky boundary layer generated by pair of oblique waves their forcing frequency sets the upper limit for the frequency of disturbances beyond which the control fails.

QC 20160208

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8

Finnis, M. V. "Centrifugal instability of a laminar boundary layer on a concave surface." Thesis, Cranfield University, 1993. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.332090.

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9

Cruz, Erica Jeannette. "Interaction of a Dynamic Vortex Generator with a Laminar Boundary Layer." Thesis, Rensselaer Polytechnic Institute, 2016. http://pqdtopen.proquest.com/#viewpdf?dispub=10159646.

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An experimental investigation was performed to study the fundamental interaction between a static and dynamic vortex generator with a laminar boundary layer. The effectiveness of static vortex generators (VGs) on delaying boundary layer separation is well established. However, as a passive flow control device, static VGs are associated with a drag penalty since they are always present in the flow. In the current study a piezoelectric-based dynamic vortex generator (DVG) was developed with the goal of mitigating the drag experienced when using a VG as a flow control device and exploring whether or not a DVG was more effective in flow mixing within the boundary layer. Experiments were conducted in a small wind tunnel, where the VG was flush mounted to the floor. The VG was rectangular in shape and erected into the flow with a mean height of the local boundary layer thickness, δ, or hm = 3 mm. The skew angle of the VG was &thetas; = 18° with respect to the incoming flow, oscillated at a driving frequency of f = 40 Hz with a peak to peak displacement (or amplitude) of 0.5·δ, or ha = 1.5 mm. During the experiments, the free stream velocity was held constant at U∞ = 10 m/s. This corresponded to a Reynolds number of Reδ ≈ 2000, which was based on the local boundary layer thickness at the center of the VG. Surface oil flow visualization experiments were performed to obtain qualitative information on the structures present in the flow, while Stereoscopic particle image velocimetry (SPIV) was used to provide quantitative measurements of the 3-D flow field at multiple spanwise planes downstream of the VG under both static and dynamic conditions. Several flow features were detected in the oil flow visualization experiments, including two vortical structures—the main vortex and primary horseshoe vortex—which were confirmed in the SPIV results. The time-averaged flow field showed similar results, though the strength of the vortices appeared less when the VG was actuated. However, phase-averaged data revealed the size, strength, and location of the vortices varied as a function of the actuation cycle, with peaks of vorticity magnitude being greater at certain phases as compared to the static case. The varying flow field associated with the dynamic motion of the DVG showed higher levels of turbulent kinetic energy, therefore confirming enhanced mixing in contrast to the static case.

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10

Bura, Romie Oktovianus. "Laminar/transitional shock-wave/boundary-layer interactions (SWBLIs) in hypersonic flows." Thesis, University of Southampton, 2004. https://eprints.soton.ac.uk/47605/.

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Numerical investigations of laminar shock-wave/boundary-layer interactions (SWBLIs) in hypersonic flow have been carried out at M∞ = 6.85 and M∞ ≈ 8, with unit Reynolds numbers ranging from 2.0 x 106 m- l to 7.60 x 106 m- l. This thesis deals with a simplified 2-D geometric configuration to simulate SWBLIs on vehicle surfaces or engine intakes, i.e. the interaction of an oblique shock (produced by a wedge) impinging on an incoming laminar boundary-layer on an isothermal flat plate. The numerical simulations were performed with weak/moderate to strong shock. The results were compared with available theoretical and experimental results. Limited experimental work at M∞ = 6.85 for obtaining qualitative data were performed to provide the location of separation and re-attachment points using surface oil flow. Schlieren photographs were taken to provide the general flow features. A comprehensive analysis was performed on the 2-D numerical results with various Mach numbers, Reynolds numbers and shock strengths, to verify whether numerical solutions were able to confirm the established trends for the laminar free-interaction concept. An analysis was also performed using a well-established power-law relationship of pressure and heat flux in the region of interactions. An unstable first oblique mode disturbance was imposed with the strongest wedge angle, 9°, at M∞ = 6.85 and unit Reynolds number 2.45 x 106 m- l to determine the boundary-layer stability and its propensity to undergo transition in the linear regime. Several unsteady 3-D simulations were performed with varied parameters. Streamwise vortices were generated in all cases especially downstream of maximum separation bubble height. However, as the amplifications of the disturbance were quite small, transition was found to be unlikely at these conditions
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Книги з теми "Laminar layer"

1

Rogers, David F. Laminar flow analysis. Cambridge: Cambridge University Press, 1992.

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2

Joslin, Ronald D. Overview of laminar flow control. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1998.

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3

1940-, Rahman M., ed. Laminar and turbulent boundary layers. Southampton: Computational Mechanics Publication, 1997.

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4

United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., ed. Distributed acoustic receptivity in laminar flow control configurations. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992.

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5

Joslin, Ronald D. Active control of instabilities in laminar boundary-layer flow. Hampton, VA: Institute for Computer Applications in Science and Engineering, NASA Langley Research Center, 1994.

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6

Theory of laminar film condensation. New York: Springer-Verlag, 1991.

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7

United States. National Aeronautics and Space Administration., ed. Parametric study on laminar flow for finite wings at supersonic speeds. [Washington, DC]: National Aeronautics and Space Administration, 1994.

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8

Ya, Levchenko V., Polyakov N. F, and United States. National Aeronautics and Space Administration., eds. Laminar boundary layer with moderate turbulence of the incoming flow. Washington, DC: National Aeronautics and Space Administration, 1989.

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9

Lin, N. Receptivity of the boundary layer on a semi-infinite flat plate with an elliptic leading edge. Tempe, Ariz: Arizona State University, Department of Mechanical and Aerospace Engineering, 1989.

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10

United States. National Aeronautics and Space Administration. Scientific and Technical Information Division., ed. A three-dimensional, compressible laminar boundary-layer method for general fuselages. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1990.

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Частини книг з теми "Laminar layer"

1

Mauri, Roberto. "Laminar Boundary Layer." In Transport Phenomena in Multiphase Flows, 137–53. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-15793-1_8.

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2

Becker, S., K. G. Condie, C. M. Stoots, and D. M. McEligot. "Reynolds stress development in the viscous layer of a transitional boundary layer." In Laminar-Turbulent Transition, 327–32. Berlin, Heidelberg: Springer Berlin Heidelberg, 2000. http://dx.doi.org/10.1007/978-3-662-03997-7_48.

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3

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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4

Babu, V. "Laminar Boundary Layer Theory." In Fundamentals of Incompressible Fluid Flow, 91–132. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-74656-8_6.

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5

Herwig, H. "Laminar Boundary Layers." In Recent Advances in Boundary Layer Theory, 9–48. Vienna: Springer Vienna, 1998. http://dx.doi.org/10.1007/978-3-7091-2518-2_2.

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6

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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7

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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8

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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9

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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10

Kumar, Rishi, and Andrew Walton. "Two-Dimensional Self-Sustaining Processes Involving Critical Layer/Wall Layer Interaction." In IUTAM Laminar-Turbulent Transition, 117–26. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-67902-6_9.

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Тези доповідей конференцій з теми "Laminar layer"

1

Sanjose, Marlene, Prateek Jaiswal, Stephane Moreau, Aaron Towne, Sanjiva K. Lele, and Adrien Mann. "Laminar boundary layer instability noise." In 23rd AIAA/CEAS Aeroacoustics Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2017. http://dx.doi.org/10.2514/6.2017-3190.

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2

Lowson, Martin, Steven Fiddes, and Emma Nash. "Laminar boundary layer aero-acoustic instabilities." In 32nd Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1994. http://dx.doi.org/10.2514/6.1994-358.

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3

Collins, J., D. Goodman, P. Delhaes, and A. P. Lee. "Nanofluidic Channel Engineering Using Laminar Flow Layer-by-Layer Deposition of Polyelectrolytes." In ASME 2004 3rd Integrated Nanosystems Conference. ASMEDC, 2004. http://dx.doi.org/10.1115/nano2004-46073.

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Layer-by-layer deposition of polyelectrolytes form multiple layers in the nanometer scale. Charged magnetic [1] and biomolecular [2] nano-colloids can be incorporated in to the layers. These multilayer assemblies are formed on the inner walls of a microchannel using laminar flow; alternatively polyanions and polycations are pumped through the channel. Water is also pumped through, between the deposition of each layer, in order to wash away the un-absorbed polyelectrolytes. The first charged layer is formed by silanation. The microfluidic device consists of a ‘T’ junction as shown in Fig. 1. Switching flow between polyelectrolytes and water is controlled by three syringe pumps, automated through a Labview virtual instrument.
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4

Ahmadvand, M., A. F. Najafi, and S. Shahidinejad. "Boundary Layer Solution for Laminar Swirling Decay Pipe Flow." In ASME/JSME 2007 5th Joint Fluids Engineering Conference. ASMEDC, 2007. http://dx.doi.org/10.1115/fedsm2007-37375.

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In this study the hydraulic-thermal developing laminar swirling pipe flow is investigated numerically. Solution is based on the integral boundary layer method Uniform and solid body rotation distributions are considered for the axial and tangential velocities at the entry, respectively. Due to wall stress, viscous region is assumed to contain two boundary layers for axial and tangential velocities. Outside of the boundary layers’ edge the flow pattern is considered to remains uniform in axial direction and forced vortex in tangential direction. Inside boundary layers parabolic velocity and temperature profiles were considered for axi-symmetric flow pattern with uniform heat flux (UHF) condition on the pipe wall. Making use of the fourth-order Runge-Kutta scheme, the numerical solution of the governing differential equations is obtained. As an alternative solution, a CFD analysis based on the finite-volume method, has been done. Finally validity of the numerical results was checked with those obtained by CFD.
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5

KIMMEL, ROGER, and JAMES KENDALL. "Nonlinear disturbances in a hypersonic laminar boundary layer." In 29th Aerospace Sciences Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1991. http://dx.doi.org/10.2514/6.1991-320.

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6

ILINCA, A., and B. BASU. "Prediction of laminar boundary layer using cubic splines." In 10th Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1992. http://dx.doi.org/10.2514/6.1992-2702.

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7

Robinet, Jean-Christophe, and P. Joubert de la Motte. "GLOBAL INSTABILITY IN SEPARATED INCOMPRESSIBLE LAMINAR BOUNDARY LAYER." In Third Symposium on Turbulence and Shear Flow Phenomena. Connecticut: Begellhouse, 2003. http://dx.doi.org/10.1615/tsfp3.510.

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8

Lopez, Maurin, and D. K. Walters. "Laminar-to-Turbulent Boundary Layer Prediction Using an Alternative to the Laminar Kinetic Energy Approach." In ASME 2012 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2012. http://dx.doi.org/10.1115/imece2012-89433.

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This paper presents a new model concept for prediction of boundary layer transition using a linear eddy-viscosity RANS approach. It is a single-point, physics-based method that adopts an alternative to the Laminar Kinetic Energy (LKE) framework. The model is based on a description of the transition process previously discussed by Walters (2009). The version of the model presented here uses the k-ω SST model as the baseline, and includes the effects of transition through one additional transport equation for v2. Here v2 is interpreted as the energy of fully turbulent, 3D velocity fluctuations, while k represents the energy of both fully turbulent and pre-transitional velocity fluctuations. This modelling approach leads to slow growth of fluctuating energy in the pre-transitional region and relaxation towards a fully turbulent model result downstream of transition. Simplicity of the formulation and ease of extension to other baseline models are two potential advantages of the new method. An initial version of the model has been implemented as a UDF subroutine in the commercial CFD code FLUENT and tested for canonical flat plate boundary layer test cases with different freestream turbulence conditions.
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9

Paxson, D. E., and R. E. Mayle. "Laminar Boundary Layer Interaction With an Unsteady Passing Wake." In ASME 1990 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1990. http://dx.doi.org/10.1115/90-gt-120.

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An investigation was conducted to study the unsteady effects of a moving wake as it passes over a laminar boundary layer in a stagnation region. Arguments are presented which show that in this region, the wake-induced unsteadiness may be treated, for the most part, as an inviscid, unsteady freestream which impresses itself on the boundary layer flow. As a result, the boundary layer equations remain valid and, for relatively small oscillations, a solution to the equations may be obtained using standard perturbation techniques. A related experiment is then described and the results are examined in light of this analytical approach.
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10

Volchkov, Eduard P., Vladimir V. Lukashov, and Vladimir V. Terekhov. "Investigation of a Laminar Boundary Layer at Hydrogen Combustion." In 2010 14th International Heat Transfer Conference. ASMEDC, 2010. http://dx.doi.org/10.1115/ihtc14-22509.

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An experimental and numerical study of a laminar boundary layer with combustion has been carried out at hydrogen and nitrogen fuel mixture blow through a porous plate. At that main flow velocity ranged from 2 to 4 m/sec and the mass fraction of hydrogen in the fuel from 1 to 11%. The lower limit of stable combustion depending on the blow intensity and hydrogen content in the fuel mixture was obtained experimentally. Data on the temperature distribution in the boundary layer have been obtained and analyzed. The simulation results show that in this range of parameters combustion occurs in the kinetic mode.
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Звіти організацій з теми "Laminar layer"

1

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

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2

Grossir, Guillaume. On the design of quiet hypersonic wind tunnels. Von Karman Institute for Fluid Dynamics, December 2020. http://dx.doi.org/10.35294/tm57.

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This document presents a thorough literature review on the development of hypersonic quiet tunnels. The concept of boundary layer transition in high-speed flows is presented first. Its consequences on the free-stream turbulence levels in ground facilities are reviewed next, demonstrating that running boundary layers along the nozzle walls must remain laminar for quiet operation. The design key points that enable laminar boundary layers and hypersonic operation with low free-stream noise levels are then identified and discussed. The few quiet facilities currently operating through the world are also presented, along with their design characteristics and performances. The expected characteristics and performances of a European quiet tunnel are also discussed, along with flow characterization methodologies and different measurement techniques. It is finally shown that the required expertise to establish the first European quiet hypersonic wind tunnel is mostly at hand.
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3

Brown, Garry L. An Experimental Study of the Receptivity of a Compressible Laminar Boundary Layer. Fort Belvoir, VA: Defense Technical Information Center, October 2008. http://dx.doi.org/10.21236/ada502767.

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4

Degrez, G., and J. J. Ginoux. Velocity Measurements in a 3D (Three Dimensional) Shock Wave Laminar Boundary Layer Interaction. Fort Belvoir, VA: Defense Technical Information Center, July 1987. http://dx.doi.org/10.21236/ada187334.

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5

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

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6

Brown, Garry L. An Experimental Study of the Receptivity of a Compressible Laminar Boundary Layer and the Effects on Stability and Receptivity of 2-D and 3-D Pressure Gradients. Fort Belvoir, VA: Defense Technical Information Center, January 2005. http://dx.doi.org/10.21236/ada431796.

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7

Stetson, Kenneth F. Hypersonic Laminar Boundary Layer Transition. Part 1. Nosetip Bluntness Effects on Cone Frustum Transition. Part 2. Mach 6 Experiments of Transition on a Cone at Angle of Attack. Fort Belvoir, VA: Defense Technical Information Center, December 1986. http://dx.doi.org/10.21236/ada178877.

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8

Wang, K. C. Three-Dimensional Laminar Boundary Layers. Fort Belvoir, VA: Defense Technical Information Center, February 1985. http://dx.doi.org/10.21236/ada175010.

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9

Noctor, Stephen C. Contributions of Early Versus Later-Generated Cortical Layers to the Development of Laminar Patterns in Ferret Somatosensory Cortex. Fort Belvoir, VA: Defense Technical Information Center, June 1998. http://dx.doi.org/10.21236/ad1012052.

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10

Schneider, Steven P., and Steven H. Collicott. Laminar-Turbulent Transition in High-Speed Compressible Boundary Layers: Continuation of Elliptic-Cone Experiments. Fort Belvoir, VA: Defense Technical Information Center, January 2000. http://dx.doi.org/10.21236/ada373478.

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