Hello,
I succeeded in realizing a mesh by modifying only the parameters that I could and I obtained the following results:
Airfoil-NACA0012 mesh: 3D elements (volumes) => 7578320
Airfoil-NACA0012 Layered mesh: 3D elements (volumes) => 8984101
Because Iâm doing the SimScale CFD Master Class training, I have to answer a question about the mesh, I would like to know if the answers are still up-to-date with the new configuration.
Hey @julien_venture,
sorry for the delayed reponse. I will contact you privately for this issue. Please check your inbox.
Cheers!
Jousef
Hi @Milad_Mafi. Can you please post here the names of books that you said in webinar I will recommend some books to learn CFD?
Thanks in Advance!
Best wishes!
Hi @Eshqin!
Not sure what my colleague @Milad_Mafi mentioned but we have some nice posts by @mananthakkar87 and @Luciano that may help you out 
I have merged some good resources in this section - have a look at âTextbooksâ. Tell me if that helped you!
All the best!
Jousef
What a great timeless video!!! I hope I can still ask questions 
I know everyone âseesâ the boundary layer differently in their mind, I just want to make sure what I âseeâ at a little more detailed level is still based somewhat on reality.
You mention the âparabolicâ shape of velocity increase in the BL at around 8:30 into your video.
I have always considered the y velocity profile to be more âasymptoticâ at both the lower 0 end and the upper freestream end. I think that regardless of how close the velocity gets to 0 or freestream, they never really get there after the freesteam passes over the flat plat. I have always considered that there would never be an air particle on the surface of the plate that would never move after a freestream was introduced over it (it may take a long time to resolve its movement, but I think it will eventually move). Any comments on what my brain âseesâ? 
Also, with regards to X distance. With the assumptions used for CFD calculations of viscous drag, is there an X distance on a flat plate where the boundary layer will separate?
Thanks,
Dale
Hi Dale (@DaleKramer)!
This is not Asad speaking in the video but my colleague Milad (@Milad_Mafi) - just to make that clear 
The âshapeâ of the velocity profile really depends on which state you are talking about. Turbulent flows usually have a velocity profile that have a higher gradient at the wall due to increased momentum transport.
On the left side you see a laminar velocity profile and on the right side a turbulent velocity profile for Poiseuille flow. Another assumption that is made when drawing these profiles is that we actually look at the âmeanâ because in fact there is a fluctuating velocity field instantaneously which looks a bit chaotic as depicted below.
This becomes important when talking about Reynolds Averaging but thatâs another topic.
Separation (same case for airfoils) requires an adverse pressure gradient to change the direction of the slow fluid to the other direction (roughly speaking). On a flat plate we assume constant pressure gradient thus no adverse pressure gradient.
P.S.: Actually good material to talk about - maybe I will do a video about such stuff in the future (if even necessary) 
Also keep in mind that Boundary Layer theory is nothing easy - just have a look at the book from Hermann Schlichting about Boundary Layer theory, have fun
Source:
Picture 2: Turbulence Modeling for CFD by David C. Wilcox
Best,
Jousef
I was not questioning what the shape was but whether the shape was asymptotic to 0 and to the freestream velocity 
But there is an X pressure gradient towards 0 shown, so I was just wondering.
Dale
Hi Dale,
we have to be careful that we are speaking of the same thing. A flat plate can also have a zero pressure gradient - inclination of the plate can either increase or decrease the pressure but can you tell me where the pressure gradient is shown to be zero? Could not find it in the video, maybe I skipped too much. Anyway if it is a zero pressure gradient we assume that âinertiaâ keeps the fluid moving although one might assume that if no pressure gradient then no driving force which is not the whole truth.
Also can you tell me exactly what you mean with asymptotic to zero at which position?
Best,
Jousef
Here is the chart from video:
All his boundary layer U magnitude as less at position x=X than at position x=0. I am just asking at some time WAY into the future what does the current assumptions of CFD show there?
For U magnitude, it would be asymptotic to 0 at y=0 and asymptotic to the freestream values for large y values.
Sorry, just started beer time and had to answer quick
Dale
Hi Dale,
maybe to sum things up: In the future you will see the boundary layer reach a maximum thickness called \delta which is different for turbulent and laminar flow over a flat plate, namely Blasius solution. The velocity profile would not change in the case of laminar or turbulent but it would when we look at transitional behavior which is again another level because this will include phenomena like the lift-up effect etc.
Also quite late here, going to bed soon - hope I did not mix up âeasyâ explanations
Best,
Jousef
Jousef,
Sorry I donât think I am asking the question so that it is decipherable. I can live without an answer but I think I will continue to âseeâ the BL as having asymptotic magnitude values approaching y=0 and y=BL thickness (ie I think asymptotic values would minimize magnitude discontinuities at the boundaries of the BL).
Thanks,
Dale
Hi Dale,
maybe itâs a misunderstanding from my side 
If you could upload a small sketch that would be of great help here
Cheers!
Jousef
in this CFD master class workshop i am done with first meshing but second meshing which content âWITH LAYERâ
are face some problem in meshing.
due to limitation i cant go with higher memory run.
please help me.
thank you,
Rohit
Hi Rohit,
please always share the project links in your posts as well, makes it way easier for us to immediately have a look at the project(s). You can decrease the level of the refinements by one and test that - I assume that you used the options given in the exercise?
Best,
Jousef
project link
Hi Rohit,
as previously mentioned reduce the refinement levels, that will do the job. What you can do is to start coarse, output a force or any other quantity and use that as some kind of convergence criterium, as long as no oscillating residuals can be observed that approach is the state of the art procedure in CFD to see when a mesh is sufficiently fine - FEA does the same but is not dependent on the residuals.
Let me know how things go!
Jousef
I will try this.
HI SIR ,
i am follow the same step as you say
I was reduce the refinement level and its work 
but there is problem in run time.
help me
thank you,
ROHIT
hi everyone,
please help me to solve above issue 
project link:
thank you,
rohit
