Vincent CFD I had to comment that it is the cleanest and the neatest mesh I have ever seen, had to say it. Thanks for the video, I am using it as base to mesh a wind turbine blade 3-D

Great video - this has helped me a bunch

Thanks for the tutorial. Can you please let me know is there any way to get straight vertical line from middle of the airfoil till end instead of getting inclined vertical line throughout the airfoil? By following your meshing steps, I'm getting inclined velocity vector profile.

Great tutorial! One thing I don't understand is why we used a pressure solver rather than a density solver in compressible flow

Hello, sir.. This is my final year project, thanks for the video as it has helped me a lot, I am facing an issue in setup, it is showing *divergence detected in amg solver... *, Can you please suggest how to get rid of the error

Inflation and face mesh are closing each other, what kind of way should be followed to solve this? I want to give inflation to my airfoil, for this I found my first layer thickness value, but the inflation is not given on top of the operations you have done, what is the reason? I am getting invalid method error.

Hi Sir, how can I set an other AoA? We have only farfield module. Is it possible to set an X and Y velocity value?

Good day! please, what was your purpose on checking the mesh metrics?

@vincentcfd9806

2 жыл бұрын

Hi, that was just to show where to pull out the mesh metric in ANSYS MESHING.

@mariarosales3535

2 жыл бұрын

@@vincentcfd9806 Thank you! if the airfoil were a simple rectangle, of the same shape as the mesh but smaller, how would be the structured mesh if all the borders were of the same # of divisions?

@vincentcfd9806

2 жыл бұрын

@@mariarosales3535 hi, you can definitely do that. You may want to project the rectangle airfoil edges onto the domain edges and split the flow domain into 8 rectangles.

sir can you please do airfoil with flap :)

is your amount of mesh cells enough sir? i mean its only around 130,000, i have done mine with a 12x8x1 m domain and 620,000 cells, my lecturer wants me to make more :') and any tutorial on utub using around 100,000-200,000, is it okay for airfoil simulation?

@vincentcfd9806

2 жыл бұрын

The video is showing how to generate structured mesh for aerofoils. For accurate cfd solutions, You will need to run the simulation once and check on the y+ value ensure it is less than 5 for lift and drag calculations. Then you need to conduct a mesh convergence study to ensure the solution is mesh independent, i.e. doesn’t change when you increase the cell count.

Hello Sir, I have two questions for you analysis- 1.The coefficient of lift for lift for you aerofoil is very less. It might be equal to 1.2 approximately. 2. Could we approach same mesh structure for a aerofoil having LE flap. Thank you! Have a great day!

@vincentcfd9806

2 жыл бұрын

1. Lift is low at zero angle of attack. Still, the results may not be accurate as mesh independent study or mesh convergence study was not done in the video. 2. Yes. You have to divide the domain to accommodate the LE flap using the same concept demonstrated in the video.

@prathamchauhan4112

2 жыл бұрын

@@vincentcfd9806 Thank you sir again!

@prathamchauhan4112

2 жыл бұрын

Sir, Can we change angle of attack with variation in X and Y components in this type of mesh. Without any errors? Have a good day Thanks,

@vincentcfd9806

2 жыл бұрын

@@prathamchauhan4112 structured mesh works best if the cells are aligned with the flow direction.

Is there supposed to be an audio?

Soooo much click click to analyze a single airfoil !!! at one angle of attack !! .. NOPE