Relevant bibliographies by topics / Onde tollmien schlichting

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  1. Journal articles
  2. Dissertations / Theses
  3. Conference papers

Academic literature on the topic 'Onde tollmien schlichting'

Author: Grafiati
Published: 4 June 2021
Last updated: 17 February 2022

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Journal articles on the topic "Onde tollmien schlichting"

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WU, XUESONG, P. A. STEWART, and S. J. COWLEY. "On the catalytic role of the phase-locked interaction of Tollmien–Schlichting waves in boundary-layer transition." Journal of Fluid Mechanics 590 (October 15, 2007): 265–94. http://dx.doi.org/10.1017/s002211200700804x.

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This paper is concerned with the nonlinear interaction between a planar and a pair of oblique Tollmien–Schlichting (T-S) waves which are phase-locked in that they travel with (nearly) the same phase speed. The evolution of such a disturbance is described using a high-Reynolds-number asymptotic approach in the so-called ‘upper--branch’ scaling regime. It follows that there exists a well-defined common critical layer (i.e. a thin region surrounding the level at which the basic flow velocity equals the phase speed of the waves to leading order) and the dominant interactions take place there. The
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Dissertations / Theses on the topic "Onde tollmien schlichting"

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DESSOLIN, JOEL. "Etude de la reduction de trainee et de la stabilite d'une couche limite laminaire sur une plaque equipee d'une serie de perturbateurs." Toulouse 3, 1998. http://www.theses.fr/1998TOU30030.

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Pour depasser le cadre de la theorie locale de la triple deck de stewartson et williams, on etablit une formulation en triple couche et en double echelle longitudinale jusqu'au second ordre des developpements asymptotiques. Celle-ci exige une utilisation precise de la regle du raccord asymptotique dont on donne l'expression appropriee. L'utilisation de developpements non reguliers, tenant compte de l'epaississement de la couche limite, s'avere particulierement bien adaptee aux ecoulements sur une plaque presentant une serie d'indentations. En effet, cette nouvelle approche montre que l'on peut
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2

Szulga, Natacha. "Étude expérimentale et numérique du contrôle de transition de couche limite par actionneurs à plasma froid surfacique." Thesis, Toulouse, ISAE, 2016. http://www.theses.fr/2016ESAE0032/document.

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La transition laminaire-turbulent au sein de la couche limite qui se développesur les parois des aéronefs augmente fortement la traînée de frottement. Ainsi, afin derépondre à une problématique à la fois environnementale et économique, une piste envisagéepour réduire la consommation en carburant des aéronefs du futur est de diminuerla trainée en reculant cette transition le plus en aval possible. Dans ce cadre, l’objectifde cette thèse est de caractériser expérimentalement et numériquement l’effet d’actionneursà plasma de type Décharge à Barrière Diélectrique sur la transition. Alimentés parun
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3

Yakhina, Gyuzel. "Experimental study of the tonal trailing-edge noise generated by low-reynolds number airfoils and comparison with numerical simulations." Thesis, Lyon, 2017. http://www.theses.fr/2017LYSEC008/document.

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Le bruit tonal rayonné au bord de fuite des profils à faible nombre de Reynolds est un phénomène observé sur les ailes de drones ou micro-drones qui sont utilisés partout dans la vie quotidienne. La diminution de ce bruit va augmenter la survivabilité et l'efficacité des appareils dans le domaine militaire. De plus, cela va augmenter le champ des applications civiles et minimiser la pollution par le bruit. La réduction efficace du bruit est indispensable et, par conséquent, une compréhension complète du processus de rayonnement du bruit tonal du profil est nécessaire. Malgré le fait que des es
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Conference papers on the topic "Onde tollmien schlichting"

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Carpenter, P. W., P. K. Sen, S. Hegde, and C. Davies. "Wave Propagation in Flows Across Junctions Between Rigid and Flexible Walls." In ASME 2002 International Mechanical Engineering Congress and Exposition. ASMEDC, 2002. http://dx.doi.org/10.1115/imece2002-32202.

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The generic problem considered is the propagation of vortical waves across junctions between one wave-bearing medium and another. It is assumed that the eigensolutions are known for the corresponding spatially homogeneous problems. The task is how to determine the amplitudes of the reflected and transmitted waves given the amplitude of the incident wave. In general, there may be more than one incident, reflected or transmitted wave. It is shown how this sort of problem may be solved in terms of the homogeneous eigensolutions by drawing an analogy between the junction and a wave-driver. The par
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2

Graveline, J. R. S., and S. A. Sjolander. "A Spectral Study of a Moderately Loaded LPT Airfoil: Part 1—Identifying Frequencies Affecting By-Pass Transition." In ASME Turbo Expo 2012: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2012. http://dx.doi.org/10.1115/gt2012-68100.

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A single wire, hot-wire, probe is used to examine the airflow in, and in close vicinity to, the shearlayer of a Low-Pressure Turbine (LPT) airfoil. A spectral analysis of the data identifies two sets of wide peaks of turbulent kinetic energy, one near 200 Hz and a second near 1 kHz. A method is developed to identify these peaks based on a combination of empirical relations between the airflow velocity and boundary layer thickness and on the location of the frequency peaks relative to the state of the free shearlayer as it transitioned from laminar to turbulent. The method suggests the presence
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3

Gostelow, J. P., and R. L. Thomas. "Interactions Between Propagating Wakes and Flow Instabilities in the Presence of a Laminar Separation Bubble." In ASME Turbo Expo 2006: Power for Land, Sea, and Air. ASMEDC, 2006. http://dx.doi.org/10.1115/gt2006-91193.

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Laminar separation was investigated experimentally on a flat plate under a strongly diffusing self-similar pressure distribution. This gave a long and thin laminar separation bubble. Boundary layer velocity traverses were performed at numerous longitudinal stations. Using a single hot wire a combination of individual traces, phase averaging and time averaging was used. To supplement this, an array of microphones was installed to give instantaneous contours of pressure perturbation and to investigate the time dependent flow features. Microphone data were consistent with the strong amplification
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4

Bettrich, Valentin, and Reinhard Niehuis. "Experimental Investigations of a High Frequency Master-Slave Fluidic Oscillator to Achieve Independent Frequency and Mass Flow Characteristics." In ASME 2016 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2016. http://dx.doi.org/10.1115/imece2016-66782.

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High frequency fluidic oscillators have been of scientific interest for many decades. Especially over the last couple of years fluidic oscillators became more important for active flow control applications. At the Institute of Jet Propulsion of the University of the German Federal Armed Forces Munich studies on different kinds of flow control methods were carried out on aerodynamically highly loaded low pressure turbine blades. On the basis of these studies, the most efficient way to trigger transition at low Reynolds numbers was found to be with fluidic oscillators at frequencies up to 10 kHz
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Mansour, Mahmoud L., S. Murthy Konan, and Shraman Goswami. "Prediction of Lapse Rate in Low Pressure Turbines With and Without Modeling of the Laminar-Turbulent Transition." In ASME Turbo Expo 2007: Power for Land, Sea, and Air. ASMEDC, 2007. http://dx.doi.org/10.1115/gt2007-27110.

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Although turbo-machinery main stream flows are predominantly turbulent, the low pressure turbine airfoil surface boundary layer may be either laminar or turbulent. When boundary layer flow is laminar and passes through a zone of adverse pressure gradient, bypass or separation transition can occur via the Tollmien-Schlichting or Kelvin-Helmholtz instabilities. As the gas turbine’s low pressure turbine operating condition changes from sea level take-off to the altitude cruise, Reynolds number is significantly lowered and the turbine’s performance loss increases significantly. This fall-off in pe
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Halstead, David E., David C. Wisler, Theodore H. Okiishi, Gregory J. Walker, Howard P. Hodson, and Hyoun-Woo Shin. "Boundary Layer Development in Axial Compressors and Turbines: Part 1 of 4 — Composite Picture." In ASME 1995 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1995. http://dx.doi.org/10.1115/95-gt-461.

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Comprehensive experiments and computational analyses were conducted to understand boundary layer development on airfoil surfaces in multistage, axial-flow compressors and LP turbines. The tests were run over a broad range of Reynolds numbers and loading levels in large, low-speed research facilities which simulate the relevant aerodynamic features of modern engine components. Measurements of boundary layer characteristics were obtained by using arrays of densely packed, hot-film gauges mounted on airfoil surfaces and by making boundary layer surveys with hot wire probes. Computational predicti
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