Congratulations, excellent contribution! We can also consider a constraint on the size of the element of the last layer, to provide a smooth transition between the elements of the layer and the surrounding mesh. It is common to choose the average size of the surrounding mesh elements. For a 2D mesh with triangular elements, let's imagine that the area of the last element of the layer has to be approximately the area of the triangular element of the mesh just around the layer, so: Area of last layer element: A = (x1+x2)*y_last, where y_last = y*G^(N-1). Area of surrounding mesh element: A = (x1+x2)*h/2 Therefore: h=2*y*G^(N-1)=2*y*(G^N)/G (for square elements h = y*G^(N-1)). Substituting G^N into equation (13), and rearranging: G = (δ-y)/(δ - h/2) and, N = 1 + log(0.5*h/y)/log(G), in previous equation note that h/2 < δ. We round off the number of layers and recalculate the growth rate: G = (0.5*h/y)^(1/(N-1))
I was revisiting this video and I have just realized that we don't actually need to use root-finding algorithm such as Newton-Raphson to solve equation (13) shown at 28:40. We can rearrange that equation and then apply logarithm to both sides, ending with: N = Ln (CG-C+1) / Ln (G). With C = delta_99 / y_H Common values for G are 1.1 or 1.2 (which is in the range you presented in the slides), so the solution is straight forward. Btw I have already implemented this new equation to my Excel sheet.
Great video, very very useful. I recently completed my Master's Degree in Aeronautical Engineering and my thesis was a CFD simulation of flow around thick airfoil. I was misunderstanding the process of mesh generation and now a lot seems more clear to me. Really great work, I hope you continue posting more and more videos and my answer to your question on whether you should continue videos on mesh generation - definitely !
Damn... Just started working on quite big project with approx. 150 layers on the airfoil profile. I think I will find this talk EXTREMELY USEFUL ;) thanks for well done job. Regards
Amazing video, I love your channel! As a high school student finding videos on fluid dynamics which are understandable is so hard, but this was perfect
This video helped me to understand meshing better and concept of inflation layer covered in this video was what I was searching on youtube. Looking forward to learn more about CFD and fluid dynamics with your help.
You are the MVP! I am working on my Bachelor Thesis and you are saving me from reading loads of dry and boring literature which I would struggle to understand. Thank you!
This video was extremely helpful. Thank you. For anybody generating meshes with Pointwise, they use the term TRex instead of inflation layers, but it's the same idea. Also, to avoid the volume ratio problems, the inflation layers (TRex) grow until the cells/prisms reach isotropy. I'm looking forward to watching more of your videos. Keep up the great work!
I have seen most of your videos and they are really very very helpful for CFD problem solving . So thank you very much for posting your videos . We would be more happy if you also post some videos on errors in CFD solvers and some more videos on the CFX or fluent software as well as how to solve errors which will not be straight forward at all . Hope to see them soon , thank you 🙏
Another problem with large volume transitions is that these volumes appear in the system matrix. Large volume transitions can result in much stiffer system matrices yielding poor iterative performance, and sometimes solver divergence.
Brilliant presentation, absolutely. Thank you so much. I would like to see more videos on Ansys Fluent Meshing, especially on local sizing including & 3D visualization of unstructured meshing and grid optimization.
I'm really fascinated with all of your videos. Big thanks! By the way, a topic "How should we do a mesh refinement study" would be very useful. In many research papers, authors do comparision base on the number of cells but not the meshing parameters
Some points I wanted to highlight: 1. If total thickness of your prismatic layers is greater then delta_99 then sudden cell volume increase shouldn't make any significant effect on friction coefficient, as friction is mostly generated in boundary layer. 2. In internal flows boundary layer usually spreads across the whole cross-section of a channel. So following your recommendations, meshes for internal flows should consist only of prism layers...
Yes to both. For 2) you normally have to have a few unstructured cells near the middle of the pipe to finish the mesh off (have a look for butterfly meshes, these are pretty popular for pipes)
Great job. Thanks for the video. I have my own excel file to calculate y+ and I guess I'll add these formulas to help me estimate my first guess for the inflation mesh =)
Great video! I would like to let you know that there is another channel called "ANSYS TUTORIAL | ANSYS COURSE | SIMULATION " that has uploaded this video. The name of the video is "Ansys | Inflation Layers Prism Layers In CFD".
Amazing Lecture, most useful for an engineering student like myself. It would be much appreciated if further meshing methodolgy videos could be uploaded. Thank you once again and keep up the excellent content.
As I expected, it was super informative video and I would love to see more from Ypu about meshing strategy! Maybe I missed something, but why huge number of layers can impact resolution of the simulation? I thought that it can only unnecessary increasy the computation time. Again Thank You for the contribution Sir!
Thank you for a nice explanation. Finally, I got a better understanding on defining a Y+. But, how to estimate Y+ for a complex geometry where flow accelerates/decelerates and defining dimension varies?
Just use your best guess. What is a representative length? How fast is the flow (roughly)? The important thing is to get the order of magnitude, not the actual value
Great summary of the topic. I'd be interested in any suggestions for meshing with a stalled wing arise. I've read some allusions to meshes being to fine. In practice reducing element size in the x direction led to stall not being apparent from the simulation. I understand that no turbulence model properly predicts stall but any advice would be good. It seems like a nebulous topic like the inflation layers.
For a rans calculation with refinement regions, does the same suggestion apply with regards to the cell volume transition? More specifically, the transition area should be placed in an area with low gradients? Also if a case has a high cell volume translation after the inflation layers, but the inflation layers span well beyond the boundary layer, is the concern lower because of the relatively low gradients? Thanks for the education!
@@fluidmechanics101 fantastic. I am really looking forward to more videos on meshing, the more CFD I do the more I realize the importance of meshing. Topics I have been asked a lot about and find interesting involve moving mesh and AMR. for AMR maybe you could talk about the different data structures and time marching techniques associated (global vs local), along with pros, cons, etc..
... technically when the flow is fully developed the boundary layer fills the entire pipe. However, for meshing the inflation layers normally a good choice is 10% of the pipe diameter
In case of the upstream flow condensation in a vertical duct, the inflation layer should cover both condensate film and boundary layer on the film surface? What would be the correct approach? Here I am talking not about the stable upstream flow where one would have stable falling film, but rather the case, where the flow velocity increases that much, that condensate begins to accumulate inside the pipe and liquid would be present across whole cross-section. Any comment would be useful. Thank you & great job with video lectures!
It sounds like you might need a pretty fine mesh resolution across your entire geometry, as you need accurate gradient calculation everywhere (you don't have a uniform freestream, which is usually assumed for boundary layer flow over a flat plate). For your case it sounds like a fully structured mesh in ICEM CFD or a hexcore mesh would be a good idea 👍
I go through Richardson extrapolation in a lot of detail in my course 'CFD for Professionals'. You can find it on Udemy or from my website. I think it is exactly what you are looking for 🙂
@@fluidmechanics101 Hi Dr Aidan, Thanks for the reply to the earlier post and I have joined for your course in udemy. I have one more doubt. I tried y+ = 1 and generated mesh in Starccm+ as per your video. When I closely observe cells in the vicinity of wall, aspect ratios are getting destroyed to a greater extent as you said in video. So my doubt is, Is there any recommended range for aspect ratios especially for cells adjacent to wall.
I'm not sure about Star CCM but most CFD codes are happy if the aspect ratio is less than 2000. You can always just try running your case and see if it runs ok? If not then try reducing the aspect ratio until you are able to get a stable solution. You can then use this solution as an initial condition for a finer mesh 👍
Thanks, but i have a few question. In this article, they used a unstructured mesh with large volume transition. I wonder why they do that, can we have a exception ? And how to handle if we make elements near the wall very very small, it will make quality bad (with prism layers) ? This is article "Investigation of ribs disturbed entrance effect of heat transfer and pressure drop in pin-fin array"
It's hard to know why without reading the paper. If they didn't state a specific reason, they probably didn't think about it at all and just made a mesh that they thought was ok ....
@@fluidmechanics101 they didn't state a specific reason :( maybe they just look at the value which they need to find. So if that value is fine, they will think mesh is fine
Hi, I’m a beginner for ANSYS fluent user. Now I’m simulating a natural convection by creating an air enclosure for a complex system. A minimum gap in my system is about 0.6 mm (between solid mating part). what method should I use to create the inflation layer?
It probably depends on the meshing software you are using 🙂 the real question is: are you sure you need to mesh the gap? Is it important? 0.6mm is quite a narrow gap ...
@@fluidmechanics101 I use the fluent meshing. If it’s possible, I will eliminate them, but I don’t know how to do this, please suggest me. One more question, I create an air enclosure and what is the boundary conditions I should apply to 6 faces of air enclosure. thank you in advance
Yes, if your gaps aren't of interest you should really try and close them up. 0.6mm gaps will be very difficult for Fluent meshing and probably give you bad cell quality. The best thing to do is probably go back to your CAD and try and close them up. It will save you a lot of trouble in the long run!
Very informative video Dr Aidan. I have doubt, if my cfd analysis involve blade with hub and shroud, do i still need to put the prism layer on the hub and shroud?
Hello, does anyone know a 3D grid generator that can provide prism layers using only hexahedrals and tetrahedrals while avoiding polyhedrals? SnappyHexMesh would be ideal but unfortunately produces polyhedra which our solver cannot handle. Thanks!
Yes. You can do this in ANSA or Fluent Meshing (formerly Tgrid). I assume that the reason for doing this is you want to use CFX and CFX can't handle polyhedral cells that are sometimes created in the buffer layer between the inflation layers and the hexcore?
@@fluidmechanics101 Awesome! Thanks for such a quick response. You're right about the solver not being able to handle polyhedral cells but I am using the hypersonics code, US3D. What would be ideal is hexahedrals on the surface with either a tetrahedral or hex core. Looks like ANSA produces tetrahedra on the surface while Fluent Meshing can do hexs on the surface. Can Fluent Meshing really do that without any polyhedral? Would be great and something on the level of GridPro.
I'm pretty sure ANSA can do hexes on the surface (if you are really careful when you make the mesh). As for fluent meshing, I am pretty sure it is possible but I am not sure of the exact TUI commands to do it
how about flow in a pipe when it comes to number of layers because at somewhere it s gonna fully developed but entrance region its developing so that will effect the size of the cell in x direction?
If I'm getting vastly different results for small variances in mesh (e.g. changing growth rate from 1.2 to 1.25 with N=7 and Yh=0.1mm causes drag to change by several percent), what is the first thing I should be looking at to reduce mesh sensitivity or to get a more trustworthy result?
If you are getting vastly different results then your flow field is probably quite different. Have a look at the flow field overall and see if you can see what is happening. Do you have flow separation? Is the separated flow very different? Once you know what is happening try and work out where you are getting most of your drag from. Then you can look at the mesh in this particular region and see how refined it is. Is your y+ locally very large? (Remember that y+ varies everywhere). Also, is your flow field unsteady or steady? You may not be resolving the flow in time and might be looking at two different snapshots. These are all just guesses as I don't know what your flow is 😅
Hi Aidan, you mentioned that dU/dY is more for RANS and hence a wall normal resolution is necessary and if we were to perform LES simulations dU/dX comes into play and resolution of cells also needs to be done along the wall. Is it a characteristic of the analysis type itself that gives rise to these gradients or does a combined dU/dY and dU/dX variation exist in flows in nature?
An easy way to think about this is to think about turbulent eddies. In LES and reality, there are very small eddies close to the wall, which we need to resolve. These have gradients in the x, y and z directions which we need to resolve. In RANS we don't resolve these eddies so we only need to resolve the gradients in the mean flow variables in the y direction
When I use the Standard k-e model and I tried to keep the first layer y+~30, that gives me a large first cell height. Do I still need 10 prism layers even if I can just use 2 to cover the boundary layer?
What is your Reynolds number and what type of flow are you trying to simulate? It sounds like you won't get the resolution you need for an accurate solution with only 2 inflation layers. Have you tried aiming for y+ ~ 1 with k omega SST instead?
@@fluidmechanics101 Thanks for your reply Aidan. I am trying to simulate a free surface LBE flow in air in a closed channel. The Re is around 60000. Based on my understanding of your video on prism layers, the prism layers need to cover the thickness of the boundary layer. So if 2 layers are enough why need 10? I tried aiming for y+~1 using sst k-w but that the first layer height is very small and I will need a large number of cells otherwise the quality of the mesh is not good. I always have this question in generating mesh for sst k-w model. That is the cell number is too large and it takes so long to run the simulation.
Hi Ran, the key to remember is that the variation of the field variables across cells in the CFD mesh is linear (at best). So in a boundary layer, where the flow variables vary steeply, you need more than 2 cells to capture the shape of the profile. You can see this if you plot a line normal to the wall through the boundary layer, the profile will be piecewise linear. The best thing I can recommend for you is to do a thorough mesh sensitivity study. You will almost definitely find that 2 inflation layers is not enough to get the wall shear stress and heat transfer coefficient correct. Yes, having y+ ~ 1 will need a lot of cells and the simulation will be slow to run, but sometimes you just have to live with this in order to get an accurate answer 🙂
Yes it will correct the wall shear stress and heat transfer coefficient on the face of the cell in contact with the wall. However if you think of the other face of the cell in contact with the wall, because the cell is 'too fat' the shear stress and heat transfer across this face will be incorrect because the cell is too large to capture the physical gradient across the cell with a linear profile. (Remember that all gradients in CFD are linear but real gradients can be much steeper, which is why we need small cells in regions of high gradient). Does this help? I know this is quite complex and isn't really explained properly anywhere, so apologies if I am still a bit confusing
Great video! My case study is tubular heat exchanger. Where can I find the equations for internal flow in order to calculate the boundary layer thickness (δ99)?
Amazing! Your videos are helping me build a strong foundation in CFD as a beginner. I have sent you a LinkedIn request. I would like to discuss and clear few doubts regarding Masters in CFD. So if you are okay with it please accept my request 🙃🙂 Thank you Dr. Aidan. Really appreciate the efforts!
I don't really use LinkedIn, so best to post your questions as precisely as possible in the comments or just send me an email (fluidmechanics101@gmail.com)
I think this is a historical question. Historically engineers would refer to block structured meshes as 'structured meshes' as a shorthand, because you could identify a particular cell in the block with an I,j,k index notation. In this sense the mesh is 'structured' by its blocks. A more modern interpretation would be that regions of a mesh with a regular 'structure' such as inflation layers could be referred to as 'structured' while the tetrahedral or polyhedral volume fill doesn't have a particular structure to it and can be referred to as 'unstructured'. Hence the mesh itself is a hybrid. Overall I think it is up to you. As long as the viewer/reader/reviewer understands how you made your mesh and where the cells are etc. you can describe it however you want. It is just semantics at the end of the day 😊
Hey, what do you think about mesh quality of the first layers of the inflation? I have performed some cases using inflation for an external flow simulation and the first layers of inflation (wedge element, similar to a pizza slice) get a low quality value. Despite of that, the flow behavior near to the ground is totally better than only using tetras. Thanks for this valuable information. Thumbs up!
Yes, the first layer often has bad quality because the cells are so thin. Usually most CFD codes are happy if the aspect ratio is less than 2000. For quality, it is worth zooming in and looking at the cells close to the wall. If the mesh lines are roughly perpendicular to the wall, then the cell quality should be fine. The difficulties tend to occur when the mesh lines close to the wall are skewed AND the aspect ratio is high. Good luck with your simulations! Don't get too put off my low quality, your simulation may still run successfully .... Give it a try!
Great video, so much to learn here. I have a question regarding the variation of y+ for mesh refinement studies though. How much do you advise the variation of y+ in different cases? for eg: for a case where I am targeting y+30, shall I take 30, 40 and 50? it would be a great help if you can clarify this. Thanks!
I think that covering an order of magnitude with your changes in y+ is a good idea. So y+ = 0.1, 0.2, 0.5 and 1.0 would be a good idea, or y+ = 30, 50, 100, 300. If you make the values too close together, then it can be difficult to see the changes in the solution. For example, y+ = 30, 35, 40, 45 probably wouldnt be as useful as 30, 50, 100 and 300. If you then find that the changes are large, you could refine you search afterwards. For example, if you tried 30, 50, 100 and 300, and the results change a lot, then you could add extra data points and try 35, 40, 45 and 55 afterwards. This is likely to be case dependent, so try it out and see what you find!
Hello Dr. Aidan, Thanks a lot for all your videos, which my colleagues and I find extremely useful! Thank you for all the time and effort you are investing in it, for the high-quality material you are producing and the clear explanations!! I have two questions regarding the topic of inflation layers: 1. When you say in pipe flow it is common practice to size the prism layers to cover 20% of the diameter, is this the height of the actual prism layer on the inner pipe wall? (which would give 40% of the diameter of the pipe covered by inflation layers if we take the layer on the opposite side, along the diameter) Or is it 20% in total, which means 10% on each "side" (10% of the diameter is the actual thickness of the prism layer) 2. In the Inflation Layer Calculator on your website (and also in the course video), I am a bit confused about the term "maximum growth ratio" : if I understand correctly, that value of G is actually calculated from the equation $ \delta_{99} = y_H \frac{1-G^N}{1-G} $. This is the value that allows the total height of the prism layers to match exactly the estimated boundary layer thickness $\delta_{99}$, with a given number of layers N chosen by the user. If I take for G a value higher than the calculated value, then my boundary layer will SURELY be contained within the inflation layers (which was actually the objective). I know it will make the mesh unnecessarily large, but I'm just saying that the objective is still fulfilled. On the other side, if I take for G a value smaller than the calculated one, the condition is not fulfilled anymore. The prism layers will not contain the entire boundary layer. So, according to my understanding, if the objective is that the inflation layers contains the entire boundary layer, shouldn't the value we are calculating actually be called "Minimum Growth Ratio" ? Thanks a lot in advance, I really highly appreciate your work and your videos.
For anyone who might have the same questions, here is the reply I received from Dr. Aidan: Hi Theo 1) It's been a long time since I wrote this video, but I'm guessing 20% means 10% on each wall. 2) I think the implication is that if you adopt a higher growth ratio than the calculated value then there would be fewer layers between the wall and the edge of the boundary layer. This would give poor accuracy. For example, if you took an extreme case and went with a growth ratio of 5, you might only have 2 or 3 layers between the wall and the boundary layer thickness. This would give a really inaccurate answer, so you should reduce G and add more layers. Kind regards Aidan
Thank you for making this video it clarify a lot of things for me. I have one question, to define the boundary layer thickness, we have to calculate Re and L, for a simple case of a flat plate, L is the length of the plate, and for pipe, its a hydraulic diameter. But in engineering application, the geometry is quite complex, if we take an example of formula 1 or engine cooling jacket, What value of L we should consider/ calculate?
The length of the car would probably be a good guess 👍 Remember that this is all to create a good initial mesh. After you have run your initial simulation it is worth looking at the mesh and checking to see if it is any good. (I.e check y+ and the velocity profiles close to the wall to see if the boundary layer is contained within the inflation layers)
You mentioned that for RANS, we want to avoid a large volume transition as it can lead to an error in the local gradients. Isn't the error dependent on the size of the cells, rather than on the growth rate? E.g. could you not have really small cells with a large growth rate, and still have small gradient error as long as the cells continue to remain small enough?
![[CFD] Aspect Ratio Warnings in CFD](http://i.ytimg.com/vi/oa3sxesYsKc/mqdefault.jpg)
![[CFD] Aspect Ratio Warnings in CFD](/img/tr.png)
![[CFD] How Fine should my CFD mesh be?](http://i.ytimg.com/vi/60fDz2cVdy8/mqdefault.jpg)
![[ ออกกอง ] วัยหนุ่ม 2544 โลกหลังลูกกรง..ทัวร์กองถ่ายหนังใน "คุกของจริง" | JUSTดูIT.](http://i.ytimg.com/vi/vB--aOkZCpw/mqdefault.jpg)
![[CFD] Pyramids, Prisms & Stair-Stepping](/img/n.gif)
Congratulations, excellent contribution!
We can also consider a constraint on the size of the element of the last layer, to provide a smooth transition between the elements of the layer and the surrounding mesh.
It is common to choose the average size of the surrounding mesh elements. For a 2D mesh with triangular elements, let's imagine that the area of the last element of the layer has to be approximately the area of the triangular element of the mesh just around the layer, so:
Area of last layer element: A = (x1+x2)*y_last, where y_last = y*G^(N-1).
Area of surrounding mesh element: A = (x1+x2)*h/2
Therefore:
h=2*y*G^(N-1)=2*y*(G^N)/G (for square elements h = y*G^(N-1)).
Substituting G^N into equation (13), and rearranging:
G = (δ-y)/(δ - h/2)
and,
N = 1 + log(0.5*h/y)/log(G), in previous equation note that h/2 < δ.
We round off the number of layers and recalculate the growth rate:
G = (0.5*h/y)^(1/(N-1))
This is awesome. I'm going to pin the comment for everyone to see
I was revisiting this video and I have just realized that we don't actually need to use root-finding algorithm such as Newton-Raphson to solve equation (13) shown at 28:40.
We can rearrange that equation and then apply logarithm to both sides, ending with:
N = Ln (CG-C+1) / Ln (G).
With C = delta_99 / y_H
Common values for G are 1.1 or 1.2 (which is in the range you presented in the slides), so the solution is straight forward.
Btw I have already implemented this new equation to my Excel sheet.
Well spotted! I spent ages trying to rearrange it into a closed form solution 😄 I have pinned your comment so everyone else can see as well
Great video, very very useful. I recently completed my Master's Degree in Aeronautical Engineering and my thesis was a CFD simulation of flow around thick airfoil. I was misunderstanding the process of mesh generation and now a lot seems more clear to me. Really great work, I hope you continue posting more and more videos and my answer to your question on whether you should continue videos on mesh generation - definitely !
i really need this to complete my undergraduate project. thank you so much.
I totally agree with your opinion... There isn't too much information on how to to do a great mesh!!! Unhappilly I've found your content just now
Thank you for the helpful in-depth explanation !❤
Your video was exactly what I needed to learn about inflation layers
Thank you! I would say this topic is essential. I looked at my meshes and it was immediately clear they need to be completely remeshed.
Damn... Just started working on quite big project with approx. 150 layers on the airfoil profile. I think I will find this talk EXTREMELY USEFUL ;) thanks for well done job. Regards
Just by the time I started learning CFD you started to add content that i had questions about. Thank you :)
Really enjoyed that, super interesting - as per normal! And yes, would love to see more on meshing
Super interesting material, excellent explanation. Many thanks.
Dr. Aidan, you are a blessing. Thank you for your contributions.💙
This is groundbreaking to me, I´m learning so much from you!
Amazing video, I love your channel! As a high school student finding videos on fluid dynamics which are understandable is so hard, but this was perfect
If you write a book I will be the first to buy a copy!
This video helped me to understand meshing better and concept of inflation layer covered in this video was what I was searching on youtube. Looking forward to learn more about CFD and fluid dynamics with your help.
Very good information.... Cleared lot of doubts in layer generation...
It is very useful for me, and I really hope you can give more talks like this.
You are the MVP! I am working on my Bachelor Thesis and you are saving me from reading loads of dry and boring literature which I would struggle to understand.
Thank you!
dude, i love you so much, thank you for all of your amazing videos
I'm really looking forward on a video about Enhanced Wall Treatment in Fluent. Keep up the great work!
there is one already uploaded on his channel!
How I wish I knew this years ago! Great information as I do my PhD by the way!
Thank you so much sir!
Wonderful video. Captured every detail.
no matter what topic you go through, I like what you say
This video was extremely helpful. Thank you. For anybody generating meshes with Pointwise, they use the term TRex instead of inflation layers, but it's the same idea. Also, to avoid the volume ratio problems, the inflation layers (TRex) grow until the cells/prisms reach isotropy. I'm looking forward to watching more of your videos. Keep up the great work!
Exactly! Thanks for your input 🙂
Really appreciate your efforts for putting this valuable knowledge online.
I have seen most of your videos and they are really very very helpful for CFD problem solving . So thank you very much for posting your videos . We would be more happy if you also post some videos on errors in CFD solvers and some more videos on the CFX or fluent software as well as how to solve errors which will not be straight forward at all . Hope to see them soon , thank you 🙏
Very useful, thank you. Looking forward to see other mesh related videos
Solid work! Thanks a lot for sharing your knowledge with us! Cheers!
Another problem with large volume transitions is that these volumes appear in the system matrix. Large volume transitions can result in much stiffer system matrices yielding poor iterative performance, and sometimes solver divergence.
I've pinned your comment, as this is another great point that was missed out 👍
Outstanding Video! thank you for making these!
Thank you so much. Would love to see more mesh related videos.
Thanks for this interesting and helpful tutorial. I really enjoyed it.
Excellent delivery
Learnt some valuable info for my dissertation, thanks 👍
Brilliant presentation, absolutely. Thank you so much. I would like to see more videos on Ansys Fluent Meshing, especially on local sizing including & 3D visualization of unstructured meshing and grid optimization.
I'm really fascinated with all of your videos. Big thanks! By the way, a topic "How should we do a mesh refinement study" would be very useful. In many research papers, authors do comparision base on the number of cells but not the meshing parameters
Very clear ! Without wall function
Great video, very useful. Please keep on .
I really loved the talk, Thank you very much.
It is quite useful!
appreciate your work.
Loved this work!!
This lecture is great!! thank you very much!!
Absolutely amazing work, thank you!
very informative, thank you for your expertise!
Thanks sir for great explanations and issues
thank you very much for your generosity in sharing this knowledge.
Some points I wanted to highlight:
1. If total thickness of your prismatic layers is greater then delta_99 then sudden cell volume increase shouldn't make any significant effect on friction coefficient, as friction is mostly generated in boundary layer.
2. In internal flows boundary layer usually spreads across the whole cross-section of a channel. So following your recommendations, meshes for internal flows should consist only of prism layers...
Yes to both. For 2) you normally have to have a few unstructured cells near the middle of the pipe to finish the mesh off (have a look for butterfly meshes, these are pretty popular for pipes)
This is a really good talk
Please consider put Star CCM+ on your CFD software list :)
Great video, thanks! This knowledge I needed :)
Thank you very much for the lesson!
Thanks for the informative video
Great job. Thanks for the video. I have my own excel file to calculate y+ and I guess I'll add these formulas to help me estimate my first guess for the inflation mesh =)
Awesome!
you are just amazing sir
Great video! I would like to let you know that there is another channel called "ANSYS TUTORIAL | ANSYS COURSE | SIMULATION " that has uploaded this video. The name of the video is "Ansys | Inflation Layers Prism Layers In CFD".
Thanks for letting me know. I really appreciate it
Amazing video! Thanks.
thank you so much you saved us a lot of time . the explication was so useful
Amazing Lecture, most useful for an engineering student like myself. It would be much appreciated if further meshing methodolgy videos could be uploaded. Thank you once again and keep up the excellent content.
Amazing Job!
... I really appreciate ur work u have all my thanks 🙏🙏🙏🙏
This is really really useful thanks for making this video!!!!
Excellent talk
Very useful!
As I expected, it was super informative video and I would love to see more from Ypu about meshing strategy! Maybe I missed something, but why huge number of layers can impact resolution of the simulation? I thought that it can only unnecessary increasy the computation time. Again Thank You for the contribution Sir!
Ah sorry for the misunderstanding. Less layers can impact resolution. More layers increases computational time
so helpful, thank you soooo much 😘
Amazing Content!
Thank you for a nice explanation.
Finally, I got a better understanding on defining a Y+.
But, how to estimate Y+ for a complex geometry where flow accelerates/decelerates and defining dimension varies?
Just use your best guess. What is a representative length? How fast is the flow (roughly)? The important thing is to get the order of magnitude, not the actual value
hello Aiden sir
Very nice video
please make the next video on CFD of combustion
Great summary of the topic. I'd be interested in any suggestions for meshing with a stalled wing arise. I've read some allusions to meshes being to fine. In practice reducing element size in the x direction led to stall not being apparent from the simulation. I understand that no turbulence model properly predicts stall but any advice would be good. It seems like a nebulous topic like the inflation layers.
great one bro
For a rans calculation with refinement regions, does the same suggestion apply with regards to the cell volume transition? More specifically, the transition area should be placed in an area with low gradients?
Also if a case has a high cell volume translation after the inflation layers, but the inflation layers span well beyond the boundary layer, is the concern lower because of the relatively low gradients?
Thanks for the education!
Yep, that seems sensible. You can get away with a sudden volume transition if you are away from the areas with high gradients that you care about 👍
@@fluidmechanics101 fantastic. I am really looking forward to more videos on meshing, the more CFD I do the more I realize the importance of meshing.
Topics I have been asked a lot about and find interesting involve moving mesh and AMR. for AMR maybe you could talk about the different data structures and time marching techniques associated (global vs local), along with pros, cons, etc..
very useful thank you!
Does anyone know where can I find empirical values of Boundary Thickness Layer for a fully developed turbulent pipe flow? Thanks!
... technically when the flow is fully developed the boundary layer fills the entire pipe. However, for meshing the inflation layers normally a good choice is 10% of the pipe diameter
In case of the upstream flow condensation in a vertical duct, the inflation layer should cover both condensate film and boundary layer on the film surface? What would be the correct approach? Here I am talking not about the stable upstream flow where one would have stable falling film, but rather the case, where the flow velocity increases that much, that condensate begins to accumulate inside the pipe and liquid would be present across whole cross-section. Any comment would be useful. Thank you & great job with video lectures!
It sounds like you might need a pretty fine mesh resolution across your entire geometry, as you need accurate gradient calculation everywhere (you don't have a uniform freestream, which is usually assumed for boundary layer flow over a flat plate). For your case it sounds like a fully structured mesh in ICEM CFD or a hexcore mesh would be a good idea 👍
This video was really helpful. please do a video on mesh independent study using Richardson extrapolation technique
I go through Richardson extrapolation in a lot of detail in my course 'CFD for Professionals'. You can find it on Udemy or from my website. I think it is exactly what you are looking for 🙂
@@fluidmechanics101 i will look into that
@@fluidmechanics101 Hi Dr Aidan,
Thanks for the reply to the earlier post and I have joined for your course in udemy. I have one more doubt. I tried y+ = 1 and generated mesh in Starccm+ as per your video. When I closely observe cells in the vicinity of wall, aspect ratios are getting destroyed to a greater extent as you said in video. So my doubt is, Is there any recommended range for aspect ratios especially for cells adjacent to wall.
I'm not sure about Star CCM but most CFD codes are happy if the aspect ratio is less than 2000. You can always just try running your case and see if it runs ok? If not then try reducing the aspect ratio until you are able to get a stable solution. You can then use this solution as an initial condition for a finer mesh 👍
Thanks, but i have a few question. In this article, they used a unstructured mesh with large volume transition. I wonder why they do that, can we have a exception ? And how to handle if we make elements near the wall very very small, it will make quality bad (with prism layers) ?
This is article "Investigation of ribs disturbed entrance effect of heat transfer and pressure
drop in pin-fin array"
It's hard to know why without reading the paper. If they didn't state a specific reason, they probably didn't think about it at all and just made a mesh that they thought was ok ....
@@fluidmechanics101 they didn't state a specific reason :( maybe they just look at the value which they need to find. So if that value is fine, they will think mesh is fine
Yep, I think you are probably 100% correct there 👍
Hi, I’m a beginner for ANSYS fluent user. Now I’m simulating a natural convection by creating an air enclosure for a complex system. A minimum gap in my system is about 0.6 mm (between solid mating part). what method should I use to create the inflation layer?
It probably depends on the meshing software you are using 🙂 the real question is: are you sure you need to mesh the gap? Is it important? 0.6mm is quite a narrow gap ...
@@fluidmechanics101 I use the fluent meshing. If it’s possible, I will eliminate them, but I don’t know how to do this, please suggest me. One more question, I create an air enclosure and what is the boundary conditions I should apply to 6 faces of air enclosure. thank you in advance
Yes, if your gaps aren't of interest you should really try and close them up. 0.6mm gaps will be very difficult for Fluent meshing and probably give you bad cell quality. The best thing to do is probably go back to your CAD and try and close them up. It will save you a lot of trouble in the long run!
Thank you so much sir!
Thank you so much sir
Thanks for your effort
Very informative video Dr Aidan. I have doubt, if my cfd analysis involve blade with hub and shroud, do i still need to put the prism layer on the hub and shroud?
Yes, if you want to calculate the total drag (and hence pressure loss) correctly
@@fluidmechanics101 thanks for the reply Dr Aidan
Hello, does anyone know a 3D grid generator that can provide prism layers using only hexahedrals and tetrahedrals while avoiding polyhedrals? SnappyHexMesh would be ideal but unfortunately produces polyhedra which our solver cannot handle. Thanks!
Yes. You can do this in ANSA or Fluent Meshing (formerly Tgrid). I assume that the reason for doing this is you want to use CFX and CFX can't handle polyhedral cells that are sometimes created in the buffer layer between the inflation layers and the hexcore?
@@fluidmechanics101 Awesome! Thanks for such a quick response. You're right about the solver not being able to handle polyhedral cells but I am using the hypersonics code, US3D. What would be ideal is hexahedrals on the surface with either a tetrahedral or hex core. Looks like ANSA produces tetrahedra on the surface while Fluent Meshing can do hexs on the surface. Can Fluent Meshing really do that without any polyhedral? Would be great and something on the level of GridPro.
I'm pretty sure ANSA can do hexes on the surface (if you are really careful when you make the mesh). As for fluent meshing, I am pretty sure it is possible but I am not sure of the exact TUI commands to do it
how about flow in a pipe when it comes to number of layers because at somewhere it s gonna fully developed but entrance region its developing so that will effect the size of the cell in x direction?
Yes, you are correct. For pipe flows, layers are normally set to cover around 20% of the diameter (which is based on the fully developed region)
@@fluidmechanics101 well-explained thank you.
If I'm getting vastly different results for small variances in mesh (e.g. changing growth rate from 1.2 to 1.25 with N=7 and Yh=0.1mm causes drag to change by several percent), what is the first thing I should be looking at to reduce mesh sensitivity or to get a more trustworthy result?
If you are getting vastly different results then your flow field is probably quite different. Have a look at the flow field overall and see if you can see what is happening. Do you have flow separation? Is the separated flow very different? Once you know what is happening try and work out where you are getting most of your drag from. Then you can look at the mesh in this particular region and see how refined it is. Is your y+ locally very large? (Remember that y+ varies everywhere). Also, is your flow field unsteady or steady? You may not be resolving the flow in time and might be looking at two different snapshots. These are all just guesses as I don't know what your flow is 😅
Hi Aidan, you mentioned that dU/dY is more for RANS and hence a wall normal resolution is necessary and if we were to perform LES simulations dU/dX comes into play and resolution of cells also needs to be done along the wall. Is it a characteristic of the analysis type itself that gives rise to these gradients or does a combined dU/dY and dU/dX variation exist in flows in nature?
An easy way to think about this is to think about turbulent eddies. In LES and reality, there are very small eddies close to the wall, which we need to resolve. These have gradients in the x, y and z directions which we need to resolve. In RANS we don't resolve these eddies so we only need to resolve the gradients in the mean flow variables in the y direction
Thanks for clearing that up!👍
Thank you!
When I use the Standard k-e model and I tried to keep the first layer y+~30, that gives me a large first cell height. Do I still need 10 prism layers even if I can just use 2 to cover the boundary layer?
What is your Reynolds number and what type of flow are you trying to simulate? It sounds like you won't get the resolution you need for an accurate solution with only 2 inflation layers. Have you tried aiming for y+ ~ 1 with k omega SST instead?
@@fluidmechanics101 Thanks for your reply Aidan. I am trying to simulate a free surface LBE flow in air in a closed channel. The Re is around 60000. Based on my understanding of your video on prism layers, the prism layers need to cover the thickness of the boundary layer. So if 2 layers are enough why need 10? I tried aiming for y+~1 using sst k-w but that the first layer height is very small and I will need a large number of cells otherwise the quality of the mesh is not good. I always have this question in generating mesh for sst k-w model. That is the cell number is too large and it takes so long to run the simulation.
Hi Ran, the key to remember is that the variation of the field variables across cells in the CFD mesh is linear (at best). So in a boundary layer, where the flow variables vary steeply, you need more than 2 cells to capture the shape of the profile. You can see this if you plot a line normal to the wall through the boundary layer, the profile will be piecewise linear. The best thing I can recommend for you is to do a thorough mesh sensitivity study. You will almost definitely find that 2 inflation layers is not enough to get the wall shear stress and heat transfer coefficient correct. Yes, having y+ ~ 1 will need a lot of cells and the simulation will be slow to run, but sometimes you just have to live with this in order to get an accurate answer 🙂
@@fluidmechanics101 Thanks again Aidan. For this case, shouldn't the wall function correct the wall shear stress and heat transfer coefficient?
Yes it will correct the wall shear stress and heat transfer coefficient on the face of the cell in contact with the wall. However if you think of the other face of the cell in contact with the wall, because the cell is 'too fat' the shear stress and heat transfer across this face will be incorrect because the cell is too large to capture the physical gradient across the cell with a linear profile. (Remember that all gradients in CFD are linear but real gradients can be much steeper, which is why we need small cells in regions of high gradient). Does this help? I know this is quite complex and isn't really explained properly anywhere, so apologies if I am still a bit confusing
Great video! My case study is tubular heat exchanger. Where can I find the equations for internal flow in order to calculate the boundary layer thickness (δ99)?
The BL fills the pipe in an internal flow. Use 20% of the pipe diameter instead as a reasonable estimate
@@fluidmechanics101Thank you for your reply! Do you have a reference that expresses this correlation?
Amazing!
Your videos are helping me build a strong foundation in CFD as a beginner.
I have sent you a LinkedIn request. I would like to discuss and clear few doubts regarding Masters in CFD.
So if you are okay with it please accept my request 🙃🙂
Thank you Dr. Aidan.
Really appreciate the efforts!
I don't really use LinkedIn, so best to post your questions as precisely as possible in the comments or just send me an email (fluidmechanics101@gmail.com)
@@fluidmechanics101 Thank you Dr. Aidan
Hello mr. Hardik Sharda
Your comments were really helpful for me to achieve proper results in cfd
Thank you so much for helping me
Would you call a unstructured mesh with inflation layers a hybrid mesh as it's a mix of the two?
I think this is a historical question. Historically engineers would refer to block structured meshes as 'structured meshes' as a shorthand, because you could identify a particular cell in the block with an I,j,k index notation. In this sense the mesh is 'structured' by its blocks.
A more modern interpretation would be that regions of a mesh with a regular 'structure' such as inflation layers could be referred to as 'structured' while the tetrahedral or polyhedral volume fill doesn't have a particular structure to it and can be referred to as 'unstructured'. Hence the mesh itself is a hybrid.
Overall I think it is up to you. As long as the viewer/reader/reviewer understands how you made your mesh and where the cells are etc. you can describe it however you want. It is just semantics at the end of the day 😊
@@fluidmechanics101 Thank you for such a detailed answer so quick! Really helpful!!!
Hey, what do you think about mesh quality of the first layers of the inflation? I have performed some cases using inflation for an external flow simulation and the first layers of inflation (wedge element, similar to a pizza slice) get a low quality value. Despite of that, the flow behavior near to the ground is totally better than only using tetras. Thanks for this valuable information. Thumbs up!
Yes, the first layer often has bad quality because the cells are so thin. Usually most CFD codes are happy if the aspect ratio is less than 2000. For quality, it is worth zooming in and looking at the cells close to the wall. If the mesh lines are roughly perpendicular to the wall, then the cell quality should be fine. The difficulties tend to occur when the mesh lines close to the wall are skewed AND the aspect ratio is high. Good luck with your simulations! Don't get too put off my low quality, your simulation may still run successfully .... Give it a try!
Brilliant.. Thanks.!
Great video, so much to learn here. I have a question regarding the variation of y+ for mesh refinement studies though. How much do you advise the variation of y+ in different cases? for eg: for a case where I am targeting y+30, shall I take 30, 40 and 50? it would be a great help if you can clarify this. Thanks!
I think that covering an order of magnitude with your changes in y+ is a good idea. So y+ = 0.1, 0.2, 0.5 and 1.0 would be a good idea, or y+ = 30, 50, 100, 300. If you make the values too close together, then it can be difficult to see the changes in the solution. For example, y+ = 30, 35, 40, 45 probably wouldnt be as useful as 30, 50, 100 and 300. If you then find that the changes are large, you could refine you search afterwards. For example, if you tried 30, 50, 100 and 300, and the results change a lot, then you could add extra data points and try 35, 40, 45 and 55 afterwards. This is likely to be case dependent, so try it out and see what you find!
@@fluidmechanics101 Thanks a lot for explaining it so clearly.
Hi
Just a quick question. If my inflation layer height is higher than my boundary layer then is that a very bad practice?
That's fine for accuracy. You might just have a few extra cells in your mesh. (More cells = slower solver)
@@fluidmechanics101 Great, thanks a lot for your response. Btw, big fan !!!
Hello Dr. Aidan,
Thanks a lot for all your videos, which my colleagues and I find extremely useful! Thank you for all the time and effort you are investing in it, for the high-quality material you are producing and the clear explanations!!
I have two questions regarding the topic of inflation layers:
1. When you say in pipe flow it is common practice to size the prism layers to cover 20% of the diameter, is this the height of the actual prism layer on the inner pipe wall? (which would give 40% of the diameter of the pipe covered by inflation layers if we take the layer on the opposite side, along the diameter) Or is it 20% in total, which means 10% on each "side" (10% of the diameter is the actual thickness of the prism layer)
2. In the Inflation Layer Calculator on your website (and also in the course video), I am a bit confused about the term "maximum growth ratio" : if I understand correctly, that value of G is actually calculated from the equation $ \delta_{99} = y_H \frac{1-G^N}{1-G} $. This is the value that allows the total height of the prism layers to match exactly the estimated boundary layer thickness $\delta_{99}$, with a given number of layers N chosen by the user. If I take for G a value higher than the calculated value, then my boundary layer will SURELY be contained within the inflation layers (which was actually the objective). I know it will make the mesh unnecessarily large, but I'm just saying that the objective is still fulfilled. On the other side, if I take for G a value smaller than the calculated one, the condition is not fulfilled anymore. The prism layers will not contain the entire boundary layer.
So, according to my understanding, if the objective is that the inflation layers contains the entire boundary layer, shouldn't the value we are calculating actually be called "Minimum Growth Ratio" ?
Thanks a lot in advance, I really highly appreciate your work and your videos.
For anyone who might have the same questions, here is the reply I received from Dr. Aidan:
Hi Theo
1) It's been a long time since I wrote this video, but I'm guessing 20% means 10% on each wall.
2) I think the implication is that if you adopt a higher growth ratio than the calculated value then there would be fewer layers between the wall and the edge of the boundary layer. This would give poor accuracy.
For example, if you took an extreme case and went with a growth ratio of 5, you might only have 2 or 3 layers between the wall and the boundary layer thickness. This would give a really inaccurate answer, so you should reduce G and add more layers.
Kind regards
Aidan
Thank you
Thank you for making this video it clarify a lot of things for me. I have one question, to define the boundary layer thickness, we have to calculate Re and L, for a simple case of a flat plate, L is the length of the plate, and for pipe, its a hydraulic diameter. But in engineering application, the geometry is quite complex, if we take an example of formula 1 or engine cooling jacket, What value of L we should consider/ calculate?
The length of the car would probably be a good guess 👍 Remember that this is all to create a good initial mesh. After you have run your initial simulation it is worth looking at the mesh and checking to see if it is any good. (I.e check y+ and the velocity profiles close to the wall to see if the boundary layer is contained within the inflation layers)
Does anyone know the previous video he is mentioning where he covered the y+ understanding?
Thanks,
You mentioned that for RANS, we want to avoid a large volume transition as it can lead to an error in the local gradients. Isn't the error dependent on the size of the cells, rather than on the growth rate? E.g. could you not have really small cells with a large growth rate, and still have small gradient error as long as the cells continue to remain small enough?