thannnnnnnnnnk you sooooooo much brother you saved me from failing semester project your method helped me a lottttttttttttttttttttttttttttttttt thank u so much
The lift and drag force calculated in the video is for half wing or for the full wing, as symmetry is used. If one wants to calculate lift and drag coefficient from the generated lift and drag force, what will be the span length (3 m or 1.5 m).
Hello, you are doing great job for beginner like me. Thank you so much. I wanted to ask about how can I calculate lift and drag with different angle of attack ? Can you please tell me from where I can change angle of attack ? Thank you so much again.
One way is to use and vary the x, y and z components of the inlet velocity and use the sine and cosine of the angle of attack - there will be other ways but that is the easiest way I have discovered (but I am only just beginning with CFD so who knows !!)
Another easy way is to directly change the angle of your airfoil in design modeller by going in create > body transformation > rotate. After rotation you can create enclosure and follow rest of the steps as shown in video. Hope that helps you. Keep sharing and supporting.
so you dont have to do this on the solution tab where you create a graph for whatever you want, you just calculate the problem and you can do this on the result-post processing part ? the number it shows you for the force, is calculated for 200 interations as well ?
Cool video. You helped me a lot! There is a question - if we have a plane of symmetry and half of the wing is involved in the calculation, then the lift is the entire wing or half?
I am glad you found it helpful. Lift is only for half wing if you simulate symmetric model. Multiply the lift value by 2 to get lift for full wing. I hope this helps.
Hello. Number of iterations depends upon when we achieve convergence. We can say convergence is achieved when all the residual values are below 1e-03 in most of the CFD simulations.
How you saved the file as stp? I cant find that format. Is it okay to continue working on the existing drawing from part 1 and continue the the part video without importing it again as stp file?
Thank you for this video. I am working on simulation of NACA 0018 airfoil our drag force value is 11.54 N but the value of Lift Force is 0.75N. If you can help me in this regard it will be helpful for me.
Hello. I think it means that your wing is causing more drag than lift. This maybe due to geometry error or very coarse mesh or inappropriate enclosure size or boundary conditions.
Hello, Thanks for this video. I am studying the flow around a 3D wing and would like help with the reference values to be specified in Ansys Fluent. I know the area is the top surface of the wing, the length is that of the chord. But my problem is that the chord is not constant all the way down the wing (the chord at the root is bigger than the salmon one). How can I specify the chord in this case, please ?
Hello Brudhel, Reference area = chord length x third direction. However if your chord length is varying then you can try to specify mean or average of chord length for your calculations and see if it matches with experimental data (if any). Hope this helps you.
Hello sir make a complete video from geometry designing to post processing in ansys fluent so that it would be very helpful to others student who are beginners. Make a complete videos related to NACA Aerofoil only sir I'm waiting for that and also how to take a values I'm ms excel and how to plot in note pad also because many student don't know they are just started to study or they don't know anything about CFD.
Hello. This video is part 2. If you check part 1 that is the previous video, you will find all the things you requested in that video. ru-vid.com/video/%D0%B2%D0%B8%D0%B4%D0%B5%D0%BE-t4iCiliEru4.html Here is the link to that video. Enjoy. Keep sharing and supporting.
Hello, thanks for the tutorial, it was really helpful for me! I have a question: how do we come back to the whole model? (What is shown at the end of the video is half of thw wing, since we are working beyond the symmetry plane only) I would like to examine the pressure distribution on the wing, streamlines and velocity vectors around the wing, but not in half wing, I want to have the complete wing. Should I go back to design modeler and not using the half of the wing, but the complete wing? Thank you so much in advance.
Just skip the symmetry operation in the design moduler and import the full model with the fluid domain and use the section plane option in the mesher for selecting the wing faces inside the flow domain
You can calculate the CL and CD value by going to reports > forces in FLUENT. Then select the correct direction vectors for lift and drag force directions and press compute. At the right side of the console window, you will be able to see the value of CL and CD getting printed.
2 года назад
@@cfdbabaopenfoamansyscfd2972 CL and CD calculating dont understand :(
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Seems like you don't have any knowledge about meshing. Where's your near wall refinements? No inflation layer, yet you're selecting k-omega SST? Do you know the required y+ value for this model? And how many layes you should generate? And do you have any idea about RANS model selection criteria? Do a little research first before making any tutorial video.
Hi. No need to be so aggressive. We all are humans and we all can improve. I know about all the things that you have mentioned. This is just Level 1 playlist for beginners. Hence I haven't considered the more detailed aspects of inflation and y+ value. The main purpose of this tutorial is to make beginners familiar with the workflow of setup for aerodynamic simulation of a simple wing. You can expect more detailed tutorial which will fulfill all your demands in near future.