Airfoil Simulation in ANSYS Fluent (C-Type Meshing)
HTML-код
- Опубликовано: 23 авг 2024
- Tutorial # 3
In this tutorial, we simulated flow over NACA 2412 airfoil and calculated its lift and drag coefficients.
Importance and meaning of reference values are discussed and many new features of design modeler are used. If your solution converges but don't get reasonable values of Cl and Cd, we strongly recommend you watch this video. A lot of other common mistakes beginners make are discussed.
If you liked the video, give it a thumbs up and don't forget to subscribe.
CSV file of airfoil coordinates can be downloaded from:
airfoiltools.co...
I tried this and it doesn't work.
Next to the Face Meshing Icon there is a small blue stop sign instead of a green tick
this was really a gr8 video....thnks for this.....can u help us with structured meshing of spherical domain over a wing in 3D? it will be highly appericiated....thnk u...
Very good tutorial. I followed the same procedure but mesh wasn't structured 😢
Will you help me regarding my problem.
I used biconvex airfoil coordinates.
C type mesh is not suitable for biconvex. Try with a rectangular domain and use face meshing. Divide the the domain into simpler constituents for better mesh.
ruclips.net/video/oOAx4j3D2rc/видео.html
@@Ansystant Thank you.
Can you provide me any source where I can find biconvex airfoil coordinates for various thickness?
I searched a lot but only 6% thickness coordinates are available.
Unfortunately the profile of many airfoils is usually not public information. The NACA airfoils are available on airfoiltools.com. People usually generate their own profile coordinates using Splines, Bezier curves etc depending upon their requirements.
@@Ansystant is there ny complete tutorial which guide perfect simulation for biconvex airfoil.?
I tried but ends up with y+ value larger than300.
I am facing the same problem, any help with meshing?
hello, can you tell me your reynold number's value?
thank you
Hii can u make a video for multi element airfoil?
Why did you use K-epsilon isn't k-omega sst a more valid model to use in this case?
can make a video on difference between c-grid meshing and o-grid meshing and also tutorial for each? i know its too much to ask😅, But if you are free; Please help
only 2d case required
hi .. i want to ask, why this amount of mesh that only contain around 110.000 mesh is not a problem? im using 12x8x1 square domain with around 620.000 mesh and my lecturer r not agree with that.. any suggestion?
can you make video on airfoil simulation and then validate it with the experimental values or from airfoiltools.com...
coz everbody is showing the airfoil analysis but noone is showing the validations... when i analysed with using clark Y airfoil( @ Re=500,000, Chord=25cm ) my values aren't matching with experimental values.
Your concern is valid. Simulations are always verified by experiments. But there is always a certain degree of error involved in experimentation or simulations. The most prominent being the effect of wing tip vortex which can not be captured by 2d simulations. If you are running experiments on wings, your results will never match with simulations done on airfoil. Let's say the wing used in wind tunnel is attached to both walls of wind tunnel (for excluding the effect of wing tip vortex), and instruments are precisely calibrated, results would be a lot closer but there will still be some error involved. And of course, it goes without saying that you have to achieve mesh independence. Keep refining mesh (especially near the airfoil) until you don't get any changes in results. Simulation in this video was done only on one mesh size. But results were still quite close (Cl=0.27 vs 0.286 on airfoiltools.com and Cd=0.0187 vs 0.0100). Mesh independence was not done for limiting video time. But refining mesh would get us exact results.
The mesh near the surface of the airfoil is way too large to capture accurate values of Cl and Cd. You need to go an online calculator (www.pointwise.com/yplus/index.html) that will give you the delta s value or the thickness of the first layer of meshing at the airfoil surface. Assume y+ = 1 then set the value you get for delta s to the thickness of the first layer of mesh. You will probably see the thickness of the mesh at the airfoil surface is way too large.
how to set the airfoil, noshear, pressure outlet, and velocity inlet in the boundary condition? mine just have interior surface body and wall surface body.
Create named selection in meshing or design modeller. Then those named walls will appear in the boundary conditions options.
I have tried it thousands of times. But when I clicked the button of generate mesh, pc became hang after generating 5% mesh. Although my laptop condition is good and other tutorials work finely. I could not understand why does this happen every time.
Crashing could mean that mesh is overloading your system memory try giving larger mesh sizing so that fewer elements get created. you can check how much system memory is used by ANSYS by windows resource monitor application.
How do you plot graph of Cl vs AoA ?
sir please tell how to do the name selections under the Mesh of airfoil. like how to name airfoil, inlet, outlet, etc. ???. Please help sir!
You can just right click on the edges you want to name and then select named selection. Or just click on the edge and press N from your keyboard.
You can also watch our video from 6:41 onwards for naming edges.
ruclips.net/video/bachu07G0y8/видео.html
@@Ansystant in design modular?
Where is the "noshear" boundary condition applied to?
You can give "pressure far-failed" condition to all boundaries other than the inlet and airfoil
Split face at geometry at 5 mins
what is your system configuration bro?
can i run this bulky mesh in ryzen 5 5600h with 8gb ram
Domain is 2d. Your system is way more than enough to run it. Even though the mesh is really fine, it's the total number of cells that increase processing requirements. For 2d meshes like these, the total cell count is not much and even most of the old computers can handle them easily.
I don't produce the same mesh as you even though I did the exact same steps. My mesh is unstructured
We can not guess the problem without adequate information. But if you follow the steps carefully, you should be able to get a structured mesh. If the problem still persists please provide us more information so we could guess the problem. We'll try to help as best as we can.
@@Ansystant I get a half structured and half unstructured mesh. Is there an email I can send the file to and you could possibly refine it?
Hi, how do you set the angle of attack?
Change the angle of airfoil from design modeller. Go to Create>body transformation>rotate and give the required angle of attack. Recreate the mesh and repeat.
@@Ansystant i heard from other youtuber that we can give
X and Y component of velocities and do the job
Please i have a probleme, when i try to upload the coord_file for the 3D curve it shows me an error "error reading coordinates file " even i did the same process as yours. If you have any idea
If you made the file according the pattern, then the error is most likely due to the same first and last point. Make sure the curve isn't closed one. If first and last point in the coordinate file are same, DM will give error. Make an open ended curve and join it later as shown in the tutorial.
No they're not the same, because i can create points but not the curve. is it possible that i have a problem in my version?
There shouldn't be a problem with ANSYS version. Upload the text file on drive and share it's link here. We'll take a look at it.
save a Coordinates in .text file like this
for example 1.0, 0.12, 0.0
0.125, 0.12, 0.0
...... , ...., 0.0
you got the X, Y coordinates from NACA and you have to add the Z (everywhere 0.0)
copy this in excel but only in one Cell (no Separate) and save like .csv(comma delimited)
@@karenmartirosyan4 you have to put them in commas not dots decimal