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Will this uncook my grades? Lets find out

Thanks for your video I've followed your steps but after I generated the mesh it keeps says 'One or more faces with ma mesh controls failed to be mapped 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" What should I do?

Fail

Hello, Anthony I watched your videos; it is very good, but is it possible to rotate the airfoil by giving different AoA? I tried doing it, but an error is popping out. I would appreciate your guidance on it. Thank you

is there any research paper associated with it

it's been 2 years since I graduated aerospace engineering and I just wanted to say, this video is the sole reason why I was able to fix an issue I had in my graduation project/capstone/bachelor thesis/dissertation. The vid is still helping me to this day, good job man

Great tutorial video. @38:22: as to why NASA and other aerospace presentations on Cp usually print the y-axis in reverse, this is to give the graphically intuitive representation of low pressure on top surface of the airfoil and high pressure on the bottom surface of the airfoil.

Hi Anthony, your video tutorial has been really useful. However, could you please explain to me what is that "wall-surface_body" we see underneath the airfoil in wall boundary conditions? why is it present? does it affect the simulation results?

NACA 2412 EX

you make me hard w these videos cheers my guy

I've found that when creating edge sizing #2 using a bias factor of 50 creates a vetter aspect ratio transition between the 2 regions

hi bro. when building geometry, you say that there's studies that show this height V1 and V2 should be at least 10 times. Can i have link to this studies?

Thanks

Make sure you save the file as UTF-8 instead of UTF-8BOM if using a .txt for importing. UTF-8BOM will fail to import to DesignModeler

can you please share the excel file linl to genrate airfoil

First of all, thank you for sharing your work. But I have a question. Even though I followed the steps exactly in the video, my Cl coefficient was calculated as 1.56. There is no problem with my CD coefficient. What do you think could be the reason for this? I would be very happy if you answer.

what is the video link of creating this 3D MODEL IN FIRST 10 SECONDS OF VIDEO? CAN YOU please share

Hi Anthony, I need help with morphing of naca 4412 for my thesis using ansys. If you have time, please let me know if we can get in contact. I am waiting for your response

how you are able to select only side of face for upper and fluid domain?

I couldn’t get a straight line of a dark mesh starting from trailing edge. My dark mesh straight line spreads towards the top right corner of the rectangular domain starting from trailing edge. I followed every steps shown on your video. It could be better if I get to contact you since I am doing my project on effect of vortex generator on wing using PIV technique. May be you can help me computationally on my project. Your help is much appreciated.🙂

Thank you. Amazing video, clear, useful and professional.

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."

Error reading coordinates file

You should work on your explanation skills,and better audio

How do I generate the mesh for 0012, should the first size be "hard"?😵‍💫

I really wish you could post a detailed video of how you did the meshing kindly guide

great video! A question: I can use these steps for different airfoils at different velocities and angle of attacks right? Also how would you adjust the Yplus to be have the first layer thin enough?

I followed the same steps as in the video but my mesh failed, showing the message : “An error occurred on the meshing”, due to computing power or something like that. I have tried to truce the number of divisions quite a lot (maximum 50) and is still not working. Any advice? I repeated the geometry and it allows me to mesh the structure, but it results in an asymmetrical meshing. I have changed the bias factor, created multiple different size Edges and still get similar results, all of them asymmetrical.

my mesh fails to generate, im using the student version 2023 R1. Could someone please help?

Can you help me complete this? Something is going wrong with my mesh on the underside of the airfoil and the fluid doesnt seem to be sticking to the airfoil in that section

why the velocity minimum in velocity contour is zero

I think you have a mistake in lift coefficient coordinates vector. If your angle of attack is positive (which is in this case like that).. The lift vector should be : cos(13) in y direction and -sin(13). Lift must be in upward-front direction (your front airfoil in negative x). So think like that. Please correct me if im wrong

Hi! How can you compute the thrust force in ANSYS in this case?

This video was informative,but the project I am currently working on has a different shape which is creating some issues for me while meshing,it is having a flat upper surface and a naca 0012 profile as the lower surface,that is it is like the naca 0012 profile exactly splitted along the chord,so will you please suggest me a domain and a how to mesh for this profile..

nice tutorial! is there some tutorial for the simulation u have opened titled "star 1"? i need a trimmed mesh of a rotating domain and i think your file is about this. thank you!

its not that your cfd data is above the real data since your graph is upside down compared to NASA's

Thanks a lot you saved hours of my time!

Please i want an answer, how to calculate the mass averaged total pressure loss, using fluent or tecplot, please anyone answers me ?!

Why do we want a Re number of 3 million? Is it just because we want it to be fully turbulent everywhere?

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.

A simple question. If i have to study any profile for different angle of attacks how would i change the angle of attacks eache time in DEsign Modeler?

The best and comprehensive tutorial found.

I am currently working on a project but after a number of analysis i am not getting the value as reference can you please help???

Do you have any suggestions how to improve the mesh for higher angles of attack? At 12 degrees I get a quite large inaccuracy between 10-30%. I tried more Divisions and a higher bias but this just leads to fluent not converging the results and the cl and cd values just go up and down in the same pattern for 1000+ iterations. I know you mentioned papers where an inaccuracy of 20-30% is still considered ok, maybe you could cite them here because I wasn’t able to find them. Thank you very much.

Thank you for providing this very informative & easy to follow tutorial! was able to get some initial results for a project based off of your work so thanks for taking the time out :)

Hey, great video man, helped me out a lot on my project. Would love to read the technical paper that you showed in the video, is there any way I can do that?

ty for maple syrup

Hello, what does it mean "quantity from interior"

does this kind of mesh work if you try to change angle of atack? I´m trying to simulate an airfoil for different Angles of Attack, but I´m having trouble with it´s mesh.

Great. I want to do this simulation on golf ball , could you please send tutorial of this simulation?