Your tutorial doesn't explain the final steps to the DesignModeller and how to split the domains. One would think this is a simple step, but of course ANSYS is so terribly made that I've been stuck for an hour trying to figure this out with no success. Surprised no one else has mentioned this in the comments. This is probably the third time I've had to rediscover this after not using ANSYS for a long time. You create "Line from Sketch" then do "Project" select all the interior lines (i.e. all the lines from Sketch2). This is exactly 0% intuitive and there is no clear answer online openly stating this anywhere that I could find, ended up going to an old model and seeing what I did. Had another engineer I know also confirm they've gotten stuck at this step lol.
Hi very nice job. could you please run the same case using the Pressure-Based instead of Density- Based and compare both results? Thanks in advance!!!!
Good day Anthony, this video has helped me understand the concept, I am trying to simulate species resulting from methane-air combustion in a simple De-laval nozzle but I am getting nowhere, could you suggest some resources I may look into? Thanks! Have a great day!
Hi Anthony, thanks for the great tutorial. There is one issue, the calculation for the gauge total pressure for the boundary condition of pressure inlet seems not correct. Since it is the total pressure, you cannot deduct the operating pressure.
Hi, I know it's a bit unclear/confusing but for ANSYS the pressure inlet has always been defined as "The total pressure value is the gauge pressure with respect to the operating pressure defined in the Operating Conditions dialog box". You can read more on the boundary condition here: www.afs.enea.it/project/neptunius/docs/fluent/html/ug/node239.htm
hi could you give me a clue how to know the suction pressure in a case of steam ejector? I am new in ansys, I search in youtube, there is one video,but in the comment section they said that's tutorial is misleading about the multiphase condition thank you so much
hi , my ansys 19.1 does'nt has "surface from sketch" , it has surface patch but I can't patch my rectangular,do you know why? "surface patch edges= 0 " In yellow notification thanks
Hi, does this flow is categorized as an under expanded flow? I still don't get a point to differentiate an under expanded and over expanded flow I thought the under expanded flow will spread all over thanks
Great video, I just have a few issues trying it myself. Could you please explain how you have identified the different boundary conditions as I have not been able to run the same as the way you have. I believe this is the error that causes a floating point exception
Nice tutorial, thank you :> I somehow have missed this validation case - so I'll have to study up. PS If you have any questions about Star-CCM+ - please feel free to contact me ;>
Hi, I’m a PhD student in the US. Some of my videos like the NACA 0012 are related to some of my research but I also enjoy improving on my CFD and sharing it.
Sir, may I ask what's the definition of grid 49x49, I saw in your tutorial you set the number of divisions to 100, however, I didn't understand the relation between 100 and 49. Could you kindly give me some hints?
49x49 is just the number of divisions for each side but while that grid might work, its still coarse or not refined very well. You want your mesh/grid to be refined enough with small enough elements to accurately capture the complex jet characteristics so that it is "mesh independent". I chose 100 somewhat arbitrarily and I have no idea how NASA chose 49. I could do 200 or really any number, but at some point the mesh is refined enough that if you make it more refined, then it won't do anything other than make it more computationally expensive. IMO 100 is sufficient to make it a good simulation, but you can play around with other levels of refinement.
@@anthonyt6564First off, thanks so much, sir, so as long as the results are accurate and the time to grow the mesh is acceptable the number of divisions won't that matter. BTW, I saw some paper using star ccm+ and OpenFOAM have this kind of grid division setting, and it somehow confused me cause recently I'm validating some cases using Ansys Fluent. I'm not quite sure but I guess the simulation was carried out by OpenFOAM since the mesh environment looks so alike.
Yes, you should be able to do a single face split operation using those 7 lines, or you can do it with 7 operations, but that is added steps. I do projections because they do the same thing.
@@salehamaarof1034 that’s something you can explore. There’s more physics behind it because compressible flows involve non-constant densities but I believe it’s simply experimentally validated that density based solvers match experimental data better.
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Your tutorial doesn't explain the final steps to the DesignModeller and how to split the domains. One would think this is a simple step, but of course ANSYS is so terribly made that I've been stuck for an hour trying to figure this out with no success. Surprised no one else has mentioned this in the comments.
This is probably the third time I've had to rediscover this after not using ANSYS for a long time. You create "Line from Sketch" then do "Project" select all the interior lines (i.e. all the lines from Sketch2). This is exactly 0% intuitive and there is no clear answer online openly stating this anywhere that I could find, ended up going to an old model and seeing what I did. Had another engineer I know also confirm they've gotten stuck at this step lol.
Dude, you are a legend
I really wish you could post a detailed video of how you did the meshing
kindly guide
Thank you. I also learned something useful in SW
Thank you for sharing such a good effort.
Amazing effort, well done!
A huge Thank you from Korea!
How did you get the curve in Solidworks it tells its self intersecting when I try to import
Thanks sir please make more videos about this ...
Great video and very informative tutorial!!!
How did you get the curve in Solidworks it tells its self intersecting when I try to import
Sir from where to get that excel file you imported in SolidWorks
Hi very nice job. could you please run the same case using the Pressure-Based instead of Density- Based and compare both results? Thanks in advance!!!!
Good day Anthony, this video has helped me understand the concept, I am trying to simulate species resulting from methane-air combustion in a simple De-laval nozzle but I am getting nowhere, could you suggest some resources I may look into?
Thanks! Have a great day!
Hi Anthony, thanks for the great tutorial. There is one issue, the calculation for the gauge total pressure for the boundary condition of pressure inlet seems not correct. Since it is the total pressure, you cannot deduct the operating pressure.
Hi, I know it's a bit unclear/confusing but for ANSYS the pressure inlet has always been defined as "The total pressure value is the gauge pressure with respect to the operating pressure defined in the Operating Conditions dialog box". You can read more on the boundary condition here: www.afs.enea.it/project/neptunius/docs/fluent/html/ug/node239.htm
hi could you give me a clue how to know the suction pressure in a case of steam ejector?
I am new in ansys, I search in youtube, there is one video,but in the comment section they said that's tutorial is misleading about the multiphase condition
thank you so much
hi , my ansys 19.1 does'nt has "surface from sketch" , it has surface patch
but I can't patch my rectangular,do you know why?
"surface patch edges= 0 " In yellow notification
thanks
Hi, does this flow is categorized as an under expanded flow? I still don't get a point to differentiate an under expanded and over expanded flow
I thought the under expanded flow will spread all over
thanks
Hello, what does it mean "quantity from interior"
What anys software are you using for this video?
Great video, I just have a few issues trying it myself. Could you please explain how you have identified the different boundary conditions as I have not been able to run the same as the way you have. I believe this is the error that causes a floating point exception
I am facing the same problem as well!!! have you able to solve it ?
Hi! How can you compute the thrust force in ANSYS in this case?
Can the sound pressure level be plotted for the jet flow
Nice tutorial, thank you :>
I somehow have missed this validation case - so I'll have to study up.
PS If you have any questions about Star-CCM+ - please feel free to contact me ;>
How do you get the curve in Solidworks it tells its self intersecting when I try to import the text document as curve
I am trying to improve myslf in cfd and I wonder, if it is not personal what do you for living?
Hi, I’m a PhD student in the US. Some of my videos like the NACA 0012 are related to some of my research but I also enjoy improving on my CFD and sharing it.
Anthony T , I see, thank you for the information . Hope to see more of your studies, and good luck with your project.
Sir, may I ask what's the definition of grid 49x49, I saw in your tutorial you set the number of divisions to 100, however, I didn't understand the relation between 100 and 49.
Could you kindly give me some hints?
49x49 is just the number of divisions for each side but while that grid might work, its still coarse or not refined very well. You want your mesh/grid to be refined enough with small enough elements to accurately capture the complex jet characteristics so that it is "mesh independent". I chose 100 somewhat arbitrarily and I have no idea how NASA chose 49. I could do 200 or really any number, but at some point the mesh is refined enough that if you make it more refined, then it won't do anything other than make it more computationally expensive. IMO 100 is sufficient to make it a good simulation, but you can play around with other levels of refinement.
@@anthonyt6564First off, thanks so much, sir, so as long as the results are accurate and the time to grow the mesh is acceptable the number of divisions won't that matter.
BTW, I saw some paper using star ccm+ and OpenFOAM have this kind of grid division setting, and it somehow confused me cause recently I'm validating some cases using Ansys Fluent.
I'm not quite sure but I guess the simulation was carried out by OpenFOAM since the mesh environment looks so alike.
You know the far field you draw, is it necessary to draw it that big?
It likely isn’t and I am not sure but that is what is drawn in the validation cases for the experimental validation
Sir, Could you explain which edges did you choose for edge sizing 11?
Hello! did you figure it out?
I get the 3-D spline curve is self-intersecting error when I import the text into Solidworks to form the curve how to overcome this
Try double checking the values from the curve. There's many videos showing how to import a curve into solidworks.
@@anthonyt6564 Got it thank you by the way can you tell how can we control the self sustaining oscillation with impinging plates
Hi can u tell me from where you get that excel file of coordinates you imported in SolidWorks
Hi
I would like to know did you do face split for every region. as I know there are 7 region. Thats means there are 7 face split?
Yes, you should be able to do a single face split operation using those 7 lines, or you can do it with 7 operations, but that is added steps. I do projections because they do the same thing.
@@anthonyt6564 yeay i did it
May I know is it same or different if need to used incompressible condition? The general part should be density based or pressure based?
@@salehamaarof1034 that’s something you can explore. There’s more physics behind it because compressible flows involve non-constant densities but I believe it’s simply experimentally validated that density based solvers match experimental data better.
Anthony T actually I have done the same thing as you did in the vid. Unfortunately I got 2 errors 1) floating point exception 2) convergence tolerance
Sir, Can you tell me your outlet boundary condition used in your simulation?
Hi, i believe I used a pressure outlet. I used whatever the validation case also used.
Is 1 bar