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Hi, is there a reason why you subtract the airfoil body? will it affect the results if i keep it?

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

I'm getting this error ‘’floating point excaption’’ How can ı this fix error

broooo you saved my life

anyone know how to send the data of the scaled residual to excel?

Hi, I found this video really helpful. However, i have encountered one issue. I am running ANSYS R19.2, i followed the exact same steps shown in the video and although i get practically the same results for Drag Coefficient and pressure coefficient, my lift coefficient is about 30% less than the one you find. Any suggestions?

Thank you. your vedio helped me a lot for my thesis project. God bless you

what a nerd hahah

is there any way where we can plot the cl vs alpha curve in ansys??

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 🙏

why the areas , depth and length are 1 bro?

Not working

Can i do the same with NACA 2415

Brilliant explanation. Kudos to your efforts and knowledge.

Hi Cillian, I watched your video on the "3D Aerofoil Tutorial in ANSYS FLUENT - NASA Onera Wing," but I'm encountering issues with the preference method you suggested. Whenever I switch from CFF to legacy, I face difficulties opening CFD. The error message I received is: "Application error(s) occurred in CFD-Post. The run 'RunSteady' in simulation 'Simulation' contains transient output, but no output files were defined." However, when I switch back to CFF, CFD post opens successfully, but I am unable to visualize the pressure coefficient on the Y-axis in CFD post. This data is crucial for validating my ongoing research work, so I would greatly appreciate your assistance with this matter. I look forward to hearing from you soon.

Hi Cillian, I watched your video, but I'm having trouble with the preference method you recommended. Every time I switch from CFF to legacy, I encounter an issue opening CFD. The error message I keep receiving is: "The run 'RunSteady' in simulation 'Simulation' contains transient output but no output files were defined." However, when I switch back to CFF, CFD post opens successfully, but I can't visualize the pressure coefficient on the Y-axis. This data is crucial for validating my ongoing research work, so your assistance on this matter would be greatly appreciated.

@20:02 Error Alert: The relation shown for phi_ext_21 should have (r**p - 1) in the denominator.

Nice video. Better at teaching Fluent than my professor.

my model doesn't have any inlet or outlet boundary conditions when it comes to my setup. Why is this?

Can u do for multi element airfoil nhlp 2d airfoil

Thanks for doing this.

How can create the same domain but in 3d I couldn't find any tutorials

Your video is helpful Thanks!

Awesome lecture and indeed a very helpful video...

can you do a video on NACA 64-618

This is an extremely bad tutorial, following all the steps the mesh doesnt even work

This is helped me out a ton. Cheers Cillian.

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

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

Thank you!

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!

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?

Fantastic video, i love i, help me a lot. But im trying with another foil, and it went wrong

Hello my face split isn't working properly, I'm using 2024 student version

Great video! Would you be able to do a video where you create the geometry in spaceclaim instead of design modeller please?

Does the coefficient of lift and drag.. change when we change the chord length ??

Please how did you create the geometry

Your videos azre very helpful!! However, I would like to ask you: Maybe you should change the bias factors??

great tutorial cilian please do one for a 3d wing too

the mesh that i create after face meshing is totally broken. can you please help me?

gj my man !!!!

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”

That Fluent cant display the reversed Bias preview annoys me every time :D But great video!

Thanks

well done

is there anyone knowing why I cant see my inlet, outlet, airfoil ?

Hi, it is an great tutorial it helped me during my engineering thesis in aeronautical engineering. One small note - when you are talking about surface of the wing - it is wing or just surface, not airfoil because airfoil is only 2D.

Hi, Thank you for your video. Can you share with us your formulation document.