Fantastic tutorial with clear explanations and loads of detail. It's refreshing to discover an ANSYS CFD video tutorial that doesn't focus solely on "what to click in ANSYS." The analysis is, instead, grounded to theory for the estimate of y+ to capture the boundary layer effect and experimental data to compare predicted values of CD and CL with actual measured values of the drag and lift coefficient of a NACA 2412 airfoil. I also appreciate that you didn't edit the portion where you iterated the vector lengths by trial and error. That's real. After conducting the entire simulation, I love that you circled back to check y+ values along the airfoil. I could heap more praise on this tutorial. It's phenomenal.
I don't know why I couldn't come accross this earlier. All this time I was spent learning from tutorials of ANSYS version 18.1 and lower. Finally found a tutorial on a newer much refined version of ANSYS. Great video Ciliian Thomas, you're a lifesafer. No amounts of 'Thank You(s)' would convey my gratitude.
I can’t thank u enough for the help I got from this. Been stressing out for a week cuz I got a workbench assignment due in two days and prior to this video I had absolutely no clue about what to do with that. But u sorted me out and I just wanna say”Thank u”
Amazing tutorial man, I have been searching for this type of session for a long time. This is a very detailed work, you amazingly explained almost every term, which is really appreciable term. Please make more, I am looking forward to diving deeper into this.
hello the video was so helpful thank you again for the great work and without your beatiful smooth way of explaining i dont think i would have understood this simulation anywhere else, one quick note tho, i have went and took a look at the paper from which you got the experimental data to compare with the simulation results and have realized that they used a 24 inch chord which is equal to about 0.61 meters but in the simulation you put in 1 meter chord i think thats why your drag coef and lift coef have that much high of an error(even though its considerdedvery low when you consider the fact that its just a simulation compared to experimental data). thanks adain for this wonderful video
Hey Cilliam, your video really helped me out. I had watched 15 plus videos on airfoils before tumbling on your video. I have to say, most of them never explained anything in detail as you did. Now, looking back at those videos, they were probably only for interacting with the gui of ansys for airfoil purposes 😂😂.
I really like this vide, appreciate your effort and time to create such useful video, please make next video on " how to improve the mesh quality such as aspect ratio, orthogonality, and skewness. Thank you
Great presentation, Try to rotate the airfoil by 8 degree at geometry from beginning and keep the inlet velocity as it is and check if you will get the same values for drag and lift coefficients
Absolutely amazing! This was a real class! I need to watch again and take notes to absorb all this knowledge you put into the video. Do you have any material indication about fluid simulation for starters?
Thanks for the very useful tutorial. Just a question: is it possible to compute the c_d and the c_l as output parameters without being costrained to change the force vectors on report definitions every time? I did parametrize velocity components as input parameters and drag&lift coefficients as output parameters, but I can't change their direction definitions (wich, as you already know, change for every angle of attack). Thank you SO much 🙏
Hi Cillian! If my chord length is 0.25m instead of 1m, does that mean that the reference value for area needs to be 0.25m^2 or keep it as 1m^2? Thanks!
I followed the tutorial step by step with the same airfoil but a chord length of 160mm and a x-velocity of 10m/s (model aircraft scale). I sized the mesh geometry accordingly (7.5, 15 times c) but my resulting Cl (0,0279) and Cd (0,00274) seem to be roughly off by a factor of 10 compared to the polars on airfoiltools in the same Reynoldsnumber and Ncrit range. Any idea what i did wrong? Is the mesh not suitable for this Re-Number regime? Again, thank you so much for the break down.
Soo I'm having a major problem with creating my my domain sketch. When turning a rectangle (in my case) from a sketch to line I get a error: "Edge could not be created due to a self intersecting curve" now I tried to replicate the rectangle and made it line by line and it always give the same error. Basically instead of having four lines (the four sides of the rectangle) I only have one. and so then I can't create the surface. I tried unistalling and reinstalling the program and even installing on a different computer and I get always the same error. It doesnt even make sense since the software creates the rectangle itself and how does it get a self intersecting curve... If anyone knows how to fix this I appreciate
I am facing a problem with the velocity and pressure contours, the velocity contour is completely blue, there's not a single red region and similarly, the pressure contour is completely green, no variation near the airfoil. What is it that I might be doing incorrectly?
Hi I actually tried this but after giving the name to section and in the silver different section name is showing rather than airfoil do you know how to resolve this issue
This video was very helpful. I am using Javafoil at the moment to generate a flap on the trailing edge of my aerofoil. Do you know of any software or method I can use to make a morphed flap, or a flap with a slight curve.
Thank you very much for your tutorial! I have question regrading the meshing step. I keep getting this error message every time I click generate mesh "The specified defeaturing tolerance was found to be larger than a specified size. The elements on one or more edges may be defeatured out." I've followed all your steps on how to create the geometry and apply the meshing conditions. But every time I try to generate the mesh, this error message keeps popping up. I really need ur guidance! Please let me know how I can correct this
@@adityatandrangi5285 @adityatandrangi5285 I solved the problem! Basically, I was changing the number of divisions of each Edge Sizing for more or less. For example, 50 more divisions in one Edge Sizing and 30 more in another. You do that arbitrarily. This way, there was a moment where the error disappeared. So, there is an optimal point where the mesh becomes quadrilateral only and there's no erro, as in the video.
Hello I have an error importing the geometry file (txt data points) into the design modeler, it can't be read, do you know what may be the issue? I followed your exact same steps and the delimiter for the decimals is the point
I wish to perfirm stress, deformation and fatigue analyses on the airfoil using different composite materials as the external covering. So is this tutorial good for that? you are doing 2D calculations right? would i need 3D for my work?
will that software allow you to add custom design vortex generators to the leading top edge of the wing and then show the pressure velocity lift co etc ?
That would relate to the geometry, Ansys has three modelers, with discovery being the newest one. Design modeler, which was used in this video works well for simple 2d and 3d models.
hey, i am actualy doing an analysis for a 3D NACA 4412 Aerofoil with chord length 150mm and span 290mm. is there any video that can show me a step by step tutorial for that. My submission is on 23rd March 🥲
Hi! Actually, I'm doing the same but with different length and span parameters and I´m also looking for a tutorial step by step. Were you able to find it? If so, let me know where to see it, please. Thanks.
@@fatihc.4301 make sure your changing the angles correctly if using sin and cos. Try meshing it better by adding inflation layer or increasing number of layers. For Eg if it’s 5 layers then make it 7 or 8.
Thats strange, they should be unlimitedly long if you are in sketch mode on the xy plane. Is it affecting your geometry though? If not I would ignore it is a bug
At 13:40 I can select vertical lines and x axes but x axes only affects left side of geometry. I cannot select right side of the x axis. That's why I couldn't manage the meshing procedure. May be using 2023 version of it can be a problem.
Fantastic tutorial with clear explanations and loads of detail. It's refreshing to discover an ANSYS CFD video tutorial that doesn't focus solely on "what to click in ANSYS." The analysis is, instead, grounded to theory for the estimate of y+ to capture the boundary layer effect and experimental data to compare predicted values of CD and CL with actual measured values of the drag and lift coefficient of a NACA 2412 airfoil. I also appreciate that you didn't edit the portion where you iterated the vector lengths by trial and error. That's real. After conducting the entire simulation, I love that you circled back to check y+ values along the airfoil. I could heap more praise on this tutorial. It's phenomenal.
I don't know why I couldn't come accross this earlier. All this time I was spent learning from tutorials of ANSYS version 18.1 and lower. Finally found a tutorial on a newer much refined version of ANSYS. Great video Ciliian Thomas, you're a lifesafer. No amounts of 'Thank You(s)' would convey my gratitude.
Nice video. Better at teaching Fluent than my professor.
I can’t thank u enough for the help I got from this. Been stressing out for a week cuz I got a workbench assignment due in two days and prior to this video I had absolutely no clue about what to do with that. But u sorted me out and I just wanna say”Thank u”
Amazing tutorial man, I have been searching for this type of session for a long time. This is a very detailed work, you amazingly explained almost every term, which is really appreciable term. Please make more, I am looking forward to diving deeper into this.
hello the video was so helpful thank you again for the great work and without your beatiful smooth way of explaining i dont think i would have understood this simulation anywhere else, one quick note tho, i have went and took a look at the paper from which you got the experimental data to compare with the simulation results and have realized that they used a 24 inch chord which is equal to about 0.61 meters but in the simulation you put in 1 meter chord i think thats why your drag coef and lift coef have that much high of an error(even though its considerdedvery low when you consider the fact that its just a simulation compared to experimental data). thanks adain for this wonderful video
This was a thoroughly explained tutorial and the results came in my first try! Thanks a lot! 😊
Hey Cilliam, your video really helped me out. I had watched 15 plus videos on airfoils before tumbling on your video. I have to say, most of them never explained anything in detail as you did. Now, looking back at those videos, they were probably only for interacting with the gui of ansys for airfoil purposes 😂😂.
After initial meshing, turn on the adaptive sizing and set the resolution to 4. Helped a lot.
Thankyou so much sir, I was stuck from last 1 week to get symmetric mesh.......Now after watching your video I finally able to get break through 😊
Brilliant explanation. Kudos to your efforts and knowledge.
Thank you. your vedio helped me a lot for my thesis project. God bless you
Thank you so much cillian. I hope you have the best of days❤
I really like this vide, appreciate your effort and time to create such useful video, please make next video on " how to improve the mesh quality such as aspect ratio, orthogonality, and skewness. Thank you
Great presentation, Try to rotate the airfoil by 8 degree at geometry from beginning and keep the inlet velocity as it is and check if you will get the same values for drag and lift coefficients
This was great, this helped me finish my assignment
Absolutely amazing! This was a real class! I need to watch again and take notes to absorb all this knowledge you put into the video. Do you have any material indication about fluid simulation for starters?
Thank you alot man, this was really informative and really helped me with my project !, cheers !
I really value your videos!! Keep up the good work!
although i did all you had done, the shape of my meshing doesn't look like yours
Truly amazing work!
Great tutorial! Keep up the fantastic work
broooo you saved my life
Great video! Would you be able to do a video where you create the geometry in spaceclaim instead of design modeller please?
Excellent tutorial. Thank you
Thanks for the very useful tutorial. Just a question: is it possible to compute the c_d and the c_l as output parameters without being costrained to change the force vectors on report definitions every time? I did parametrize velocity components as input parameters and drag&lift coefficients as output parameters, but I can't change their direction definitions (wich, as you already know, change for every angle of attack). Thank you SO much 🙏
my model doesn't have any inlet or outlet boundary conditions when it comes to my setup. Why is this?
You should name inlet and the outlet in mesh step already
@rand1633 I figured this out, too. Thanks for the reply anyway.
@@spriinter11 wlc
i did everyting same but when i tried to use 'face split' , i have 7 different faces, no 6. Idk why What should i do
Hi Cillian!
If my chord length is 0.25m instead of 1m, does that mean that the reference value for area needs to be 0.25m^2 or keep it as 1m^2?
Thanks!
great tutorial cilian
please do one for a 3d wing too
Thanks for doing this.
make one video of simulating on air foil which has surface modifications
I followed the tutorial step by step with the same airfoil but a chord length of 160mm and a x-velocity of 10m/s (model aircraft scale). I sized the mesh geometry accordingly (7.5, 15 times c) but my resulting Cl (0,0279) and Cd (0,00274) seem to be roughly off by a factor of 10 compared to the polars on airfoiltools in the same Reynoldsnumber and Ncrit range. Any idea what i did wrong? Is the mesh not suitable for this Re-Number regime? Again, thank you so much for the break down.
make sure your reference value length in fluent is 160mm instead of the default
i am getting reversed flow problem. i followed all the setting can you suggest anything. does changing domain size effect coefficient of lift.
How can create the same domain but in 3d I couldn't find any tutorials
Soo I'm having a major problem with creating my my domain sketch. When turning a rectangle (in my case) from a sketch to line I get a error: "Edge could not be created due to a self intersecting curve" now I tried to replicate the rectangle and made it line by line and it always give the same error. Basically instead of having four lines (the four sides of the rectangle) I only have one. and so then I can't create the surface. I tried unistalling and reinstalling the program and even installing on a different computer and I get always the same error. It doesnt even make sense since the software creates the rectangle itself and how does it get a self intersecting curve... If anyone knows how to fix this I appreciate
Why my mesh warning shows "1. one or more faces with map mesh controls failed to be mapped mesh. 2. The Quad mesher failed on one or more faces."
I am facing a problem with the velocity and pressure contours, the velocity contour is completely blue, there's not a single red region and similarly, the pressure contour is completely green, no variation near the airfoil. What is it that I might be doing incorrectly?
tons of things to learn, thanks,
Hi I actually tried this but after giving the name to section and in the silver different section name is showing rather than airfoil do you know how to resolve this issue
This video was very helpful. I am using Javafoil at the moment to generate a flap on the trailing edge of my aerofoil. Do you know of any software or method I can use to make a morphed flap, or a flap with a slight curve.
the mesh that i create after face meshing is totally broken. can you please help me?
Thank you very much for your tutorial! I have question regrading the meshing step. I keep getting this error message every time I click generate mesh "The specified defeaturing tolerance was found to be larger than a specified size. The elements on one or more edges may be defeatured out."
I've followed all your steps on how to create the geometry and apply the meshing conditions. But every time I try to generate the mesh, this error message keeps popping up.
I really need ur guidance! Please let me know how I can correct this
Really need to know this too. Same here.
I have got the same issue.Did you find the solution for it?
@@adityatandrangi5285 @adityatandrangi5285 I solved the problem! Basically, I was changing the number of divisions of each Edge Sizing for more or less. For example, 50 more divisions in one Edge Sizing and 30 more in another. You do that arbitrarily. This way, there was a moment where the error disappeared. So, there is an optimal point where the mesh becomes quadrilateral only and there's no erro, as in the video.
@@adityatandrangi5285 If the error is still there, just tell me here.
Fantastic video, i love i, help me a lot.
But im trying with another foil, and it went wrong
That Fluent cant display the reversed Bias preview annoys me every time :D
But great video!
Hi! How to resolve "fluent application failed to validate the connection" when running the setup? Thanks
Can you share the text file of airfoils? I really can't do this ı always get self interecting error
Thanks for sharing.
Please can you provide videos on dynamic mesh.
Hi, great video, I have a question, why is it -SIn(8) for the X direction and not Sin(8)? Where did the minus come from?
help jsjs
Can you do 3D simulation and CFD for a blended wing body or a VTOL? or may be a flying wing. Please
Does the coefficient of lift and drag.. change when we change the chord length ??
How can i create drag-atack of angle graphic
how did you find the line should be 80 inches from the start
Can you tell that why's the minimum velocity contour value coming out to be 0?
Hello I have an error importing the geometry file (txt data points) into the design modeler, it can't be read, do you know what may be the issue? I followed your exact same steps and the delimiter for the decimals is the point
hey i got the exact same error, i knoww its been really long but did you figure it out? and if u did could you let me know what was wrong?
is there any way where we can plot the cl vs alpha curve in ansys??
I wish to perfirm stress, deformation and fatigue analyses on the airfoil using different composite materials as the external covering. So is this tutorial good for that? you are doing 2D calculations right? would i need 3D for my work?
More importantly, I loved your tutorial, kindly advise me on how to study the 3D simulations
what u do for different angle of attack? changing the inlet velocity directions?
is there anyone knowing why I cant see my inlet, outlet, airfoil ?
anyone know how to send the data of the scaled residual to excel?
will that software allow you to add custom design vortex generators to the leading top edge of the wing and then show the pressure velocity lift co etc ?
That would relate to the geometry, Ansys has three modelers, with discovery being the newest one. Design modeler, which was used in this video works well for simple 2d and 3d models.
Is 3e06 and 3*10^6 same in ANSYS? ..... Please reply
what a great video sir, but why can i input my coordinate file? it said error reading coordinate file
and can you explain what is 0,8 i'll appreciate that
@@bagusalfateh5144 Hi. I am having the same error, did you solve it?
Thank you!
Hello my face split isn't working properly, I'm using 2024 student version
My either, did you ever figure it out?
Im facing the same issue, and due to that, my mesh isn't showing up. Did u guys figure it out
Thanks for the tutorial! With regards to mesh quality, does it not matter that the aspect ratio all around the mesh will be very high?
It wont matter in the boundary layer only since the flow direction is along the stretched direction of the elements
@@cillianthomasengineering Thank you for the response, could you possibly refer me to literature explaning more about this?
@20.19, when selecting 4 edges, on left side it is showing only two edges in geometry even though mentioned 4 edges. could someone clarify this?
Noticed it too. He might have missed pressing ctrl when selecting.
Does anyone know how you would then use this information to work out torque?
how can we reach out to you pls?
Can u do for multi element airfoil nhlp 2d airfoil
Can i do the same with NACA 2415
Sir how to change AOA in 3D?
gj my man !!!!
why the areas , depth and length are 1 bro?
Also How do i do a mesh independant study?
hey, i am actualy doing an analysis for a 3D NACA 4412 Aerofoil with chord length 150mm and span 290mm.
is there any video that can show me a step by step tutorial for that.
My submission is on 23rd March 🥲
Could you fine answer? Also I do 3d 2214 analysis. I can get lift coef. with %1 error but drag coef. %50 error
Hi!
Actually, I'm doing the same but with different length and span parameters and I´m also looking for a tutorial step by step. Were you able to find it? If so, let me know where to see it, please.
Thanks.
you guys find anything
@@fatihc.4301 make sure your changing the angles correctly if using sin and cos. Try meshing it better by adding inflation layer or increasing number of layers. For Eg if it’s 5 layers then make it 7 or 8.
@@CarlosAlvarez-vf8wk I just did the same thing from this video but In 3D
Bro how did you select this whole x axis? I couldnt extrude this X axis.
What time stamp of the video is this at?
For example at 8:40. Mine X and Y axes are short. But yours are unlimitedly long
Thats strange, they should be unlimitedly long if you are in sketch mode on the xy plane. Is it affecting your geometry though? If not I would ignore it is a bug
At 13:40 I can select vertical lines and x axes but x axes only affects left side of geometry. I cannot select right side of the x axis. That's why I couldn't manage the meshing procedure. May be using 2023 version of it can be a problem.
brother use meteras the unit for design modeler whereas use millimeter when creating 3d curve for airfoil
Not working
what a nerd hahah
This is an extremely bad tutorial, following all the steps the mesh doesnt even work
Did u figure it out my mesh isn't even showing up