Author: Anthony Beaudoin
Publisher:
ISBN:
Category :
Languages : fr
Pages :
Book Description
L'objectif de la thèse est la résolution des problèmes de transport dans les milieux poreux à l'aide des méthodes particulaires. Deux problèmes sont résolus avec les méthodes particulaires : la migration d'un soluté dans une nappe phréatique et l'écoulement de l'eau dans un milieu poreux à l'échelle des pores. Pour résoudre l'équation de convection-dispersion dans le cas général d'une dispersion anisotrope, un algorithme basé sur les méthodes particulaires et la méthode de vitesse de dispersion est présenté. Pour simuler l'écoulement dans un milieu poreux à des faibles nombres de Reynolds, un algorithme basé sur une méthode particulaire anisotrope et une méthode intégrale de frontière est présenté. La méthode particulaire anisotrope permet d'améliorer la description de la couche limite se formant autour des grains du sol. La méthode intégrale de frontière permet de satisfaire la condition d'adhérence en écrivant une équation intégrale de frontière sur le contour des grains du sol
Contribution numérique à l'étude du transport de masse dans les milieux poreux saturés
Author: Anthony Beaudoin
Publisher:
ISBN:
Category :
Languages : fr
Pages :
Book Description
L'objectif de la thèse est la résolution des problèmes de transport dans les milieux poreux à l'aide des méthodes particulaires. Deux problèmes sont résolus avec les méthodes particulaires : la migration d'un soluté dans une nappe phréatique et l'écoulement de l'eau dans un milieu poreux à l'échelle des pores. Pour résoudre l'équation de convection-dispersion dans le cas général d'une dispersion anisotrope, un algorithme basé sur les méthodes particulaires et la méthode de vitesse de dispersion est présenté. Pour simuler l'écoulement dans un milieu poreux à des faibles nombres de Reynolds, un algorithme basé sur une méthode particulaire anisotrope et une méthode intégrale de frontière est présenté. La méthode particulaire anisotrope permet d'améliorer la description de la couche limite se formant autour des grains du sol. La méthode intégrale de frontière permet de satisfaire la condition d'adhérence en écrivant une équation intégrale de frontière sur le contour des grains du sol
Publisher:
ISBN:
Category :
Languages : fr
Pages :
Book Description
L'objectif de la thèse est la résolution des problèmes de transport dans les milieux poreux à l'aide des méthodes particulaires. Deux problèmes sont résolus avec les méthodes particulaires : la migration d'un soluté dans une nappe phréatique et l'écoulement de l'eau dans un milieu poreux à l'échelle des pores. Pour résoudre l'équation de convection-dispersion dans le cas général d'une dispersion anisotrope, un algorithme basé sur les méthodes particulaires et la méthode de vitesse de dispersion est présenté. Pour simuler l'écoulement dans un milieu poreux à des faibles nombres de Reynolds, un algorithme basé sur une méthode particulaire anisotrope et une méthode intégrale de frontière est présenté. La méthode particulaire anisotrope permet d'améliorer la description de la couche limite se formant autour des grains du sol. La méthode intégrale de frontière permet de satisfaire la condition d'adhérence en écrivant une équation intégrale de frontière sur le contour des grains du sol
Dynamics and Control of Underactuated Multibody Spacecraft
Filtering for Some Stochastic Processes with Discrete Observations
Author: Oleg V. Makhnin
Publisher:
ISBN:
Category : Filters (Mathematics)
Languages : en
Pages : 130
Book Description
Publisher:
ISBN:
Category : Filters (Mathematics)
Languages : en
Pages : 130
Book Description
On Propagating Instabilities in Nickel-titanium & Steel Alloys
Author: Mark Anthony Iadicola
Publisher:
ISBN:
Category :
Languages : en
Pages : 412
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 412
Book Description
Guidance Strategies for Microburst Escape
Performance Prediction of a Ducted Rocket Combustor [microform]
Author: Robert Alan Stowe
Publisher: National Library of Canada = Bibliothèque nationale du Canada
ISBN: 9780612654341
Category :
Languages : en
Pages : 420
Book Description
Publisher: National Library of Canada = Bibliothèque nationale du Canada
ISBN: 9780612654341
Category :
Languages : en
Pages : 420
Book Description
Fixed-structure Adaptive-improvement Control
A Numerical Investigation of Sound Generation in Supersonic Jet Screech
Author: Ted A. Manning
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
Book Description
The noise of supersonic jet flows is due in part to the interaction between jet instability waves and the jet shock-cell structure. If no countermeasures are taken, the emitted shock-cell noise will re-excite certain instability wave modes at the nozzle lip and cause resonant feedback to occur. This feedback resonance, known as supersonic jet screech, causes the jet to flap violently at discrete frequencies and generate very strong, narrow banded tones. Jet screech has been shown to be a source of acoustic fatigue in the tail and nozzle structures of supersonic aircraft. It is important that methods for predicting the screech amplitude be developed. Screech sound generation is one such element. We isolate the interaction of an unsteady shear layer with a single oblique shock. To obtain an overall understanding of the phenomenon with fewest simplifications, we study this problem through the numerical solution of the Navier Stokes equations. We then consider idealizations which allow us to obtain a similar but wider range of results with specially linearized Euler equations. The findings of these r0sults motivate the use of geometric acoustics to describe the screech generation process. The Navier-Stokes and Euler simulations have revealed important details about the interaction process, how the acoustic field results, and why screech is so loud. The mechanism for sound production is found to be fundamentally different and more efficient when the instability waves are the large vortices typical of screech, than when they are small disturbances. Geometrical acoustics can be used to explain the leakage effect at high instability wave amplitude. We conclude that the mechanism for high amplitude screech generation is an unsteady modification to the velocity field by the instability waves that permits the incident shock to refract through the shear layer.
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
Book Description
The noise of supersonic jet flows is due in part to the interaction between jet instability waves and the jet shock-cell structure. If no countermeasures are taken, the emitted shock-cell noise will re-excite certain instability wave modes at the nozzle lip and cause resonant feedback to occur. This feedback resonance, known as supersonic jet screech, causes the jet to flap violently at discrete frequencies and generate very strong, narrow banded tones. Jet screech has been shown to be a source of acoustic fatigue in the tail and nozzle structures of supersonic aircraft. It is important that methods for predicting the screech amplitude be developed. Screech sound generation is one such element. We isolate the interaction of an unsteady shear layer with a single oblique shock. To obtain an overall understanding of the phenomenon with fewest simplifications, we study this problem through the numerical solution of the Navier Stokes equations. We then consider idealizations which allow us to obtain a similar but wider range of results with specially linearized Euler equations. The findings of these r0sults motivate the use of geometric acoustics to describe the screech generation process. The Navier-Stokes and Euler simulations have revealed important details about the interaction process, how the acoustic field results, and why screech is so loud. The mechanism for sound production is found to be fundamentally different and more efficient when the instability waves are the large vortices typical of screech, than when they are small disturbances. Geometrical acoustics can be used to explain the leakage effect at high instability wave amplitude. We conclude that the mechanism for high amplitude screech generation is an unsteady modification to the velocity field by the instability waves that permits the incident shock to refract through the shear layer.
Adaptive Harmonic Balance Method for Unsteady, Nonlinear, One- Dimensional Periodic Flows
Author: Raymond C. Maple
Publisher:
ISBN: 9781423508137
Category : Fluid dynamics
Languages : en
Pages : 167
Book Description
A new adaptive split-domain harmonic balance computational fluid dynamics (CFD) method is developed to solve highly nonlinear time-periodic flows such as those found in turbomachinery. The basic harmonic balance CFD method transforms an unsteady time-periodic problem into a steady-state problem by assuming a solution in the form of a Fourier series in time. The new method employs a unique multi-domain split-operator solution technique to remove a large-series stability restriction present in previous harmonic balance CFD approaches. In addition, the new method adapts the frequency content to the flow, starting with a small number of Fourier frequencies and augmenting the frequency content in each cell as necessary to capture local flow physics. The method reduces compute times by allowing larger integration time steps, eliminating Fourier transforms, and reducing overall problem size. The stability and accuracy of the method are verified with solutions to the 1-D inviscid Burger's equation and 1-D Euler's equation. Accurate adapted quasi-1-D Euler solutions for a supersonic/subsonic diverging nozzle with periodic unsteady outflow conditions are generated in 86% less time than an equivalent non-adapted split-domain solution, demonstrating the performance benefit of matching frequency content to the local flow conditions.
Publisher:
ISBN: 9781423508137
Category : Fluid dynamics
Languages : en
Pages : 167
Book Description
A new adaptive split-domain harmonic balance computational fluid dynamics (CFD) method is developed to solve highly nonlinear time-periodic flows such as those found in turbomachinery. The basic harmonic balance CFD method transforms an unsteady time-periodic problem into a steady-state problem by assuming a solution in the form of a Fourier series in time. The new method employs a unique multi-domain split-operator solution technique to remove a large-series stability restriction present in previous harmonic balance CFD approaches. In addition, the new method adapts the frequency content to the flow, starting with a small number of Fourier frequencies and augmenting the frequency content in each cell as necessary to capture local flow physics. The method reduces compute times by allowing larger integration time steps, eliminating Fourier transforms, and reducing overall problem size. The stability and accuracy of the method are verified with solutions to the 1-D inviscid Burger's equation and 1-D Euler's equation. Accurate adapted quasi-1-D Euler solutions for a supersonic/subsonic diverging nozzle with periodic unsteady outflow conditions are generated in 86% less time than an equivalent non-adapted split-domain solution, demonstrating the performance benefit of matching frequency content to the local flow conditions.