Пікірлер

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  @mihapirnar891511 күн бұрын

  I have a question. When you click "Sizing" and then under "Definition" i don't have "Body of Infuence". What should i do?

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  @mo7ametto822Ай бұрын

  Very well benefit of this , thx sir 👍🏻

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  @boowboow311Ай бұрын

  sir can you please do airfoil with flap :)

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  @harigovardhan82162 ай бұрын

  In this how to find the cd and cl of the tyre..?

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  @juliafarrugia90692 ай бұрын

  Why did you include the UDS, after the velocity at the outlet, converged? Does it not work if you include the UDS from the start? Thank you

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  @barryz66252 ай бұрын

  Promo_SM 😣

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  @doguhanozms42383 ай бұрын

  I find the cd values to low with slang angle 80 degree I changed just chamber part in design modeler, I have used same mesh but cd is coming 0.28 it is too low with this slant angle how ı can change?

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  @vishalsk27833 ай бұрын

  Waiting for the next part

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  @RafaelSanchez-zu9jo3 ай бұрын

  amazing!!! Thank you so much for sharing this!!!!!!!!!

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  @Filis863 ай бұрын

  Hi thanks for this.

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  @mo7ametto8223 ай бұрын

  Thx for sharing sir 🤝🏻

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  @saskhkh61243 ай бұрын

  Great job

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  @jakubskobyko87343 ай бұрын

  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?

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  @AdamButt044 ай бұрын

  The drag coefficient is too low?

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  @doguhanozms42383 ай бұрын

  how did you change

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  @AdamButt043 ай бұрын

  @@doguhanozms4238frontal area should be 0.056 in ansys reference values… Because we halved the ahmed’s body

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  @ahmetkirhan58964 ай бұрын

  Thanks for this tutorial. I didn't understand one part. How did you manage to set x axis starting from 0 to 1 or default setting is like this?

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  @madladdan8 ай бұрын

  mine gets stuck on "attaching to assembly" ?

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  @prakashghose75189 ай бұрын

  In our work, the density is constant. So the source of mean air age will be constant everywhere. Kindly explain..

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  @farahyoussef169410 ай бұрын

  this was super helpful thank you!!

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  @dhrubosaha21010 ай бұрын

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

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  @thegamze5515 Жыл бұрын

  Can I get 4 instead of 36 in setup? does this cause a problem? I can't run it because I'm a student licensed.

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  @PawanKumar-io7gu2 ай бұрын

  no

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  @berkekahvecioglu8946 Жыл бұрын

  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.

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  @KadlagNikhil Жыл бұрын

  How did you calculate the value of area?? If my cylinder is of D diameter what should be the area in D???

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  @Catloverss95 Жыл бұрын

  Create an unstructured mesh of Gable low-rise building (Convert to Polyhedral mesh) kzread.info/dash/bejne/h3qLj6uMhKiuoZM.html

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  @Catloverss95 Жыл бұрын

  Create an unstructured mesh of Gable low-rise building (Convert to Polyhedral mesh) kzread.info/dash/bejne/h3qLj6uMhKiuoZM.html

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  @monalisa_m__m Жыл бұрын

  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

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  @milknice7813 Жыл бұрын

  The first layer height in your video is 0.4mm, but it should be 0.04mm or less if you want the y+ value to be around 30,right?

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  @youarebeautiful3191 Жыл бұрын

  After building this, is it possible to do a cavitation analysis of it

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  @adilabeldinov2966 Жыл бұрын

  hi everyone, who can make rans and urans simulation of Ahmed body with discrete adjoint optimization?

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  @laibazafar7402 Жыл бұрын

  Next part

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  @laibazafar7402 Жыл бұрын

  Where is IFSTREAM?

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  @adwaithdr1291 Жыл бұрын

  The drag coefficient should be around 1.3 for Re= 100

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  @mustafaalnasser749 Жыл бұрын

  Excellent tutorial, one of the greatest actually.

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  @hishaamkhalid5772 Жыл бұрын

  Kindly tell what you did between 10 35 minutes and 10 45 minutes?

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  @trungmai3420 Жыл бұрын

  How long do you run the simulation?

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  @realtalk4193 Жыл бұрын

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

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  @kherrafi.abdelbassit Жыл бұрын

  ❤❤❤❤❤❤❤❤❤❤❤❤❤

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  @mohamadabdulrahim5869 Жыл бұрын

  what if uref is changing over time in a transient simulation? how can we do this in the udf? pls any advice

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  @vincentcfd9806 Жыл бұрын

  If Uref is changing over time, you will need to create a function that takes “time” as input argument and return the value of Uref. You can refer to the manual here: www.afs.enea.it/project/neptunius/docs/fluent/html/udf/node243.htm

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  @mohamadabdulrahim5869 Жыл бұрын

  what if uref is changing over time in a transient simulation? how can we do this in the udf? pls help

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  @knightpokemon1250 Жыл бұрын

  says failed to process a boi, boi either too thin or open? can you help me with this

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  @LeviAckerman-qg7ho Жыл бұрын

  Plz bring more lectures

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  @tilakghote4646 Жыл бұрын

  Sir, how can i contact you?

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  @vincentcfd9806 Жыл бұрын

  You can contact me at [email protected]

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  @nidhinkakkanattu21782 жыл бұрын

  There is considerable error in the cd value

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  @AdamButt044 ай бұрын

  did you find out how to fix this?

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  @nidhinkakkanattu21784 ай бұрын

  @@AdamButt04 did it long back. It is all about meshing

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  @AdamButt044 ай бұрын

  @@nidhinkakkanattu2178thanks for replying, I’ll try look at the meshing today and fix it.

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  @abdullahalmugairin83882 жыл бұрын

  Is there supposed to be an audio?

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  @ricardowallff19002 жыл бұрын

  That's wonderfull and surprising imagen ever seen bye me!

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  @prathamchauhan41122 жыл бұрын

  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!

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  @vincentcfd98062 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.

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  @prathamchauhan41122 жыл бұрын

  @@vincentcfd9806 Thank you sir again!

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  @prathamchauhan41122 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,

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  @vincentcfd98062 жыл бұрын

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

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  @muhammadsyihabfachry38842 жыл бұрын

  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?

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  @vincentcfd98062 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.

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  @tirumalad24792 жыл бұрын

  Can you send me the ansys file please? I'm getting lot of errors

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  @zhongxichao19762 жыл бұрын

  Many thanks for the video, especially the shared ABL!!!

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  @erikci_furkan2 жыл бұрын

  Thank you

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  @lalitjagtap98882 жыл бұрын

  can you please send the files on drive