http://www.cfd-online.com/W/index.php?title=Special:Contributions/Bingmicrosoft&feed=atom&limit=50&target=Bingmicrosoft&year=&month=CFD-Wiki - User contributions [en]2016-10-01T01:54:55ZFrom CFD-WikiMediaWiki 1.16.5http://www.cfd-online.com/Wiki/Best_practice_guidelines_for_heat_transfer_simulationsBest practice guidelines for heat transfer simulations2011-04-07T02:21:15Z<p>Bingmicrosoft: </p>
<hr />
<div>{{stub}}<br />
Heat Transfer is a engineering branch which deals with flow of Heat through any material.<br />
Heat is form of energy that gets transformed from a body at higher temperature to a body a lower temperature.<br />
There are three modes of heat transfer namely- Conduction, Convection and Radiation.<br />
<br />
Conduction takes place due to two mechanisms in the solids. They are inter molecualar interaction and by drift of free electrons. When there is a temperature difference the molecules starts moving from place to place and results in the interactions where the energy exchange takes place between these molecules which results in energy transfer. The other way is, if you fundamental knowledge of the nucleas, every substance having nucleas and number of orbits surrounding it like planets surrounding sun. As we go far from the nucleas the molucules having less energy. So when there is a temperature difference, the electrons will shift from one energy level to other energy level which results in the energy difference. These are the two ways by which the conduction heat transfer takes place. Fourier law governs the conduction heat transfer.<br />
<br />
Convection heat transfer exists only when there is a motion of fluid from place to place on a solid. When a fluid is moving on a solid (say both are at the different temperature), there exists a temperature gradient between these two media and results in the energy transfer. If this fluid motion is created by some external agents like fan or pump, it is forced convection and if the fluid motion arises because of the density variation and there by due to buyoyancy effects, it is free convection. Newtons law of cooling governs the convection heat transfer. <br />
<br />
Radiation heat trasfer doesn't require any type of media. In this mode the energy transfer takes place through the electro magnetic waves. Radiation heat transfer will exists only at higher temperatures and it will be maximum in the vaccum. Stefan's Boltzman law governs the Raditation heat transfer.</div>Bingmicrosofthttp://www.cfd-online.com/Wiki/Best_practice_guidelines_for_heat_transfer_simulationsBest practice guidelines for heat transfer simulations2011-04-07T02:16:37Z<p>Bingmicrosoft: </p>
<hr />
<div>{{stub}}<br />
Heat Transfer is a engineering branch which deals with flow of Heat through any material.<br />
Heat is form of energy that gets transformed from a body at higher temperature to a body a lower temperature.<br />
There are three modes of heat transfer namely- Conduction, Convection and Radiation.<br />
<br />
Conduction takes place due to two mechanisms in the solids. They are inter molecualar interaction and by drift of free electrons. When there is a temperature difference the molecules starts moving from place to place and results in the interactions where the energy exchange takes place between these molecules which results in energy transfer. The other way is, if you fundamental knowledge of the nucleas, every substance having nucleas and number of orbits surrounding it like planets surrounding sun. As we go far from the nucleas the molucules having less energy. So when there is a temperature difference, the electrons will shift from one energy level to other energy level which results in the energy difference. These are the two ways by which the conduction heat transfer takes place. Fourier law governs the conduction heat transfer.<br />
<br />
Convection heat transfer exists only when there is a motion of fluid from place to place on a solid. When a fluid is moving on a solid (say both are at the different temperature), there exists a temperature gradient between these two media and results in the energy transfer. If this fluid motion is created by some external agents like fan or pump, it is forced convection and if the fluid motion arises because of the density variation and there by due to buyoyancy effects, it is free convection. Newtons law of cooling governs the convection heat transfer. <br />
<br />
Radiation heat trasfer doesn't require any type of media. In this mode the energy transfer takes place through the electro magnetic waves. Radiation heat transfer will exists only at higher temperatures and it will be maximum in the vaccum. Stefan's Boltzman law governs the Raditation heat transfer.<br />
[http://www.seomediasite.com search engine optimisation agency]<br />
[http://xhomehealthcare.com/weight-loss/proactol-scam proactol scam]</div>Bingmicrosofthttp://www.cfd-online.com/Wiki/Best_practice_guidelines_for_heat_transfer_simulationsBest practice guidelines for heat transfer simulations2011-04-07T02:15:23Z<p>Bingmicrosoft: </p>
<hr />
<div>{{stub}}<br />
Heat Transfer is a engineering branch which deals with flow of Heat through any material.<br />
Heat is form of energy that gets transformed from a body at higher temperature to a body a lower temperature.<br />
There are three modes of heat transfer namely- Conduction, Convection and Radiation.<br />
<br />
Conduction takes place due to two mechanisms in the solids. They are inter molecualar interaction and by drift of free electrons. When there is a temperature difference the molecules starts moving from place to place and results in the interactions where the energy exchange takes place between these molecules which results in energy transfer. The other way is, if you fundamental knowledge of the nucleas, every substance having nucleas and number of orbits surrounding it like planets surrounding sun. As we go far from the nucleas the molucules having less energy. So when there is a temperature difference, the electrons will shift from one energy level to other energy level which results in the energy difference. These are the two ways by which the conduction heat transfer takes place. Fourier law governs the conduction heat transfer.<br />
----<br />
<br />
<br />
Convection heat transfer exists only when there is a motion of fluid from place to place on a solid. When a fluid is moving on a solid (say both are at the different temperature), there exists a temperature gradient between these two media and results in the energy transfer. If this fluid motion is created by some external agents like fan or pump, it is forced convection and if the fluid motion arises because of the density variation and there by due to buyoyancy effects, it is free convection. Newtons law of cooling governs the convection heat transfer. <br />
<br />
Radiation heat trasfer doesn't require any type of media. In this mode the energy transfer takes place through the electro magnetic waves. Radiation heat transfer will exists only at higher temperatures and it will be maximum in the vaccum. Stefan's Boltzman law governs the Raditation heat transfer.</div>Bingmicrosofthttp://www.cfd-online.com/Wiki/Aero-acoustics_and_noiseAero-acoustics and noise2011-04-07T02:13:11Z<p>Bingmicrosoft: /* Hydrodynamic/acoustic splitting */</p>
<hr />
<div>== Introduction ==<br />
Sound can be understood as the pressure fluctuation in a medium. Acoustics is the study of sound propagation in a medium; AeroAcoustics deals with the study of noise generated by air. Examples include the flow around the landing gear of an aircraft, or the buffeting noise caused when driving along with the window/sunroof open. As a result of the stringent conditions imposed on the Aircraft industries to limit noise pollution, focus is now shifting towards predicting the noise generated by a given aerodynamic flow. Similarly, in the automotive industry, passenger comfort is of great importance, so OEMs are keen to minimise unnecessary noise sources.<br />
<br />
AeroAcoustics is an advanced field of fluid dynamics in which the flow scale is removed to the acoustic levels. The first advance in the field of AeroAcoustics was made by Sir James Lighthill when he presented an &quot;Acoustic Analogy&quot;. With proper manipulation of the Euler equations, he derived a wave equation based on pressure as the fluctuating variable, and the flow variables contributing to the source of fluctuation. The resulting wave equation can then be integrated with the help of Green's Function, or can be integrated numerically. Thus, this equation can represent the sound propagation from a source in an ambient condition. With the success of the acoustic analogy, many improvements were made on the derivation of the wave equation. Two common form of the equation used in the acoustic analogy are the Ffowcs Williams - Hawkins equation and the Kirchoff's Equation. <br />
<br />
Although the Acoustic Analogy solves the problem of noise prediction to a great extent, focus is now shifting towards direct computation, in which noise is computed directly by the flow solver. Of course the acoustic analogy is still applied in far field propagation, but near field sound generation is resolved to a large extent. Large Eddy Simulation is widely used for these studies. DNS is still unuseable for problems of practical dimensions; industries require a code that can provide them results in a day, not a month. Hence, RANS based models (like JET3D by NASA) are widely used in industry.<br />
<br />
One of the main difficulties in Computational AeroAcoustics is the scale of the problem. Acoustic waves have a high velocity relative to the flow structures and, at the same time, are nearly 10 orders of magnitude smaller. Also, due to the propagation to long distances, the numerical scheme should be less dissipative and less dispersive. The CFD solvers have inherent dissipation to ensure stability. This makes most robust CFD solvers incapable of simulating acoustic flows. Advanced schemes such as Dispersion Relation Preserving (DRP) schemes, compact schemes etc., aim at a less dispersive solution. Still, given the limits of current computational capability, acoustic computation for a problem of practical interest is still out of reach.<br />
<br />
The solution adopted by the main code vendors (STAR-CD, Fluent, CFX) is to de-couple the problem: solve for the acoustic sources in the CFD code, then couple to an acoustic propagation code (SYSNoise, Actran) to discover noise levels some distance from the source.<br />
<br />
== Different Methods ==<br />
=== DNS ===<br />
<br />
=== Green's Function ===<br />
=== [[Hydrodynamic/acoustic splitting]] ===<br />
The hydrodynamic/acoustic splitting method (also known as viscous/acoustic splitting) has been originally proposed by Hardin and Pope (1994) for resolving the issue of scale disparity in low Mach number aeroacoustics. This method splits the direct numerical simulation (DNS) into the viscous-hydrodynamic and inviscid-acoustic calculations. The viscous flow field is computed by solving the incompressible Navier-Stokes equations, while the acoustic field is obtained by the perturbed compressible equations (PCE). This splitting method has further been modified by Shen and Sorenson (1999) and Slimon et al (1999).<br />
Recently, Seo and Moon (2005) proposed the Linearized Perturbed Compressible Equation (LPCE). The LPCE <br />
simulates the noise generation and propagation from the incompressible flow field solution in a natural way, and also could secure <br />
a consistent acoustic solution with suppressing the evolution of unstable vortical mode in the perturbed system. Since this method <br />
is based on the incompressible flow solution, it is very effective for the flows at low Mach numbers. Moreover, computational <br />
efficiency can further be enhanced, if grid system for the flow and acoustics are treated separately for resolving the scale <br />
disparity at low Mach numbers.<br />
<br />
==Higher Order Schemes for Aero-acoustics==<br />
=== Finite Difference ===<br />
<br />
=== Finite Volume ===<br />
<br />
==Boundary Conditions ==<br />
== Reference ==<br />
<br />
{{stub}}</div>Bingmicrosofthttp://www.cfd-online.com/Wiki/Aero-acoustics_and_noiseAero-acoustics and noise2011-04-07T02:12:10Z<p>Bingmicrosoft: /* Hydrodynamic/acoustic splitting */</p>
<hr />
<div>== Introduction ==<br />
Sound can be understood as the pressure fluctuation in a medium. Acoustics is the study of sound propagation in a medium; AeroAcoustics deals with the study of noise generated by air. Examples include the flow around the landing gear of an aircraft, or the buffeting noise caused when driving along with the window/sunroof open. As a result of the stringent conditions imposed on the Aircraft industries to limit noise pollution, focus is now shifting towards predicting the noise generated by a given aerodynamic flow. Similarly, in the automotive industry, passenger comfort is of great importance, so OEMs are keen to minimise unnecessary noise sources.<br />
<br />
AeroAcoustics is an advanced field of fluid dynamics in which the flow scale is removed to the acoustic levels. The first advance in the field of AeroAcoustics was made by Sir James Lighthill when he presented an &quot;Acoustic Analogy&quot;. With proper manipulation of the Euler equations, he derived a wave equation based on pressure as the fluctuating variable, and the flow variables contributing to the source of fluctuation. The resulting wave equation can then be integrated with the help of Green's Function, or can be integrated numerically. Thus, this equation can represent the sound propagation from a source in an ambient condition. With the success of the acoustic analogy, many improvements were made on the derivation of the wave equation. Two common form of the equation used in the acoustic analogy are the Ffowcs Williams - Hawkins equation and the Kirchoff's Equation. <br />
<br />
Although the Acoustic Analogy solves the problem of noise prediction to a great extent, focus is now shifting towards direct computation, in which noise is computed directly by the flow solver. Of course the acoustic analogy is still applied in far field propagation, but near field sound generation is resolved to a large extent. Large Eddy Simulation is widely used for these studies. DNS is still unuseable for problems of practical dimensions; industries require a code that can provide them results in a day, not a month. Hence, RANS based models (like JET3D by NASA) are widely used in industry.<br />
<br />
One of the main difficulties in Computational AeroAcoustics is the scale of the problem. Acoustic waves have a high velocity relative to the flow structures and, at the same time, are nearly 10 orders of magnitude smaller. Also, due to the propagation to long distances, the numerical scheme should be less dissipative and less dispersive. The CFD solvers have inherent dissipation to ensure stability. This makes most robust CFD solvers incapable of simulating acoustic flows. Advanced schemes such as Dispersion Relation Preserving (DRP) schemes, compact schemes etc., aim at a less dispersive solution. Still, given the limits of current computational capability, acoustic computation for a problem of practical interest is still out of reach.<br />
<br />
The solution adopted by the main code vendors (STAR-CD, Fluent, CFX) is to de-couple the problem: solve for the acoustic sources in the CFD code, then couple to an acoustic propagation code (SYSNoise, Actran) to discover noise levels some distance from the source.<br />
<br />
== Different Methods ==<br />
=== DNS ===<br />
<br />
=== Green's Function ===<br />
=== [[Hydrodynamic/acoustic splitting]] ===<br />
The hydrodynamic/acoustic splitting method (also known as viscous/acoustic splitting) has been originally proposed by Hardin and Pope (1994) for resolving the issue of scale disparity in low Mach number aeroacoustics. This method splits the direct numerical simulation (DNS) into the viscous-hydrodynamic and inviscid-acoustic calculations. The viscous flow field is computed by solving the incompressible Navier-Stokes equations, while the acoustic field is obtained by the perturbed compressible equations (PCE). This splitting method has further been modified by Shen and Sorenson (1999) and Slimon et al (1999). [http://google.com [color=transparent]google[/color]]<br />
Recently, Seo and Moon (2005) proposed the Linearized Perturbed Compressible Equation (LPCE). The LPCE <br />
simulates the noise generation and propagation from the incompressible flow field solution in a natural way, and also could secure <br />
a consistent acoustic solution with suppressing the evolution of unstable vortical mode in the perturbed system. Since this method <br />
is based on the incompressible flow solution, it is very effective for the flows at low Mach numbers. Moreover, computational <br />
efficiency can further be enhanced, if grid system for the flow and acoustics are treated separately for resolving the scale <br />
disparity at low Mach numbers.<br />
<br />
==Higher Order Schemes for Aero-acoustics==<br />
=== Finite Difference ===<br />
<br />
=== Finite Volume ===<br />
<br />
==Boundary Conditions ==<br />
== Reference ==<br />
<br />
{{stub}}</div>Bingmicrosoft