Sir I cannot express my gratitude towards You in plain words! You have helped me do one of the most critical simulations for my project. I will be crediting You and citing the video link in the future for my project! Thank You and please keep the good work going on!
Hi, I really appreciate everything you post in your channel. You videos are very informative and I've learned a lot from them. I would like to ask if you can please to show me the required steps to draw the flowing grid H-O-H and J-grid mesh. Best Regards.
Can this method be used to calculate lift, moment and drag coefficient of a dynamic aerofoil? I need to find the coefficient values for changing the angle of attacks and different pitching rates.
Hello. Thank you for the video. I have a question. It is possible to put the moving circular zone in motion not with a constant value of 0.5 rad/s but using a UDF function which assign an angular velocity in function of time? Thank you.
Hi, Thank you very much for this tutorial. But I tried to do this in 3D but I get a problem of negative cell in the calculation step. What you can advice?
Depends on the angles of attack you want to sweep through. But this person set it up such that the time step was 0.005 sec, with 400 iterations. 0.005 sec*400= 2 sec. 0.5 rad/s * 2 sec= 1 rad. 1 rad = 57.2958 degrees. I believe this is the logic.
Thanks for the video sir .but while creating the fluid surface and rotating surface. I'm getting an error like" intersecting profile is not allowed" or sometimes "invalid profile selection"!! PL help me in this regard
Hey bro, Sorry I am not asking related question... I want to simulate NACA 0012 and 0015 at stall angel in ansys fluent, Which models should I use and how refined mesh should be? Speed of air is 50m/s. Thanx in advance.
hey, I did a analysis on tapered wing, with NACA 23012. laminar model with 57 m/s velocity inlet. but the Cl values I get is in the range of 100..y is that.. is there any solution for it?
Hello Sir! Do you think it would be possible to share the mp3 video? I would like to use it to explain my students flow separation and pressure gradients with variations in AoA :D
Hello I did the analytical of a NACA 4415 in drag fluid and lifting the results these Cl = 7.2870e-04 and Cd = 1.7649e-05 The experimental results are Cl = 0.787785 Cd = 0.01218 I would like to know how to interpret these fluid values and whether they are correct or approximate with the experiments
@@htc2930 excuse me sir, how to use this method on dynamics mesh or moving mesh please help me some advice. thank you very much if you reply me i'm a student.
I want to analyse a four bladed dareius turbine using fluent. However, I want to know how to go by the geometrical drawing using ansys designmodeler or autocad. Any good link? Thanks
This in CATIA and Solidworks: th-cam.com/video/GFyNCK2qrEs/w-d-xo.html th-cam.com/video/GUkWRQc2QAY/w-d-xo.html If you want to know how to create an airfoil in DesignModeler, check this: th-cam.com/video/thrB-mKHGek/w-d-xo.html Or send me your model's picture that you want to design.
thanks for the tutorial but i have a problem at 10:58 you edit the airfoil that is a wall but when i click edit for airfoil there are no options appear. I can't figure out why it is not showing me anything i check the mesh and named selections they look okay like you do. Do you have opinion about whats causing it ?
I fixed something was wrong in my geomety nut now it is working fine. I actually want to calculate cl cd cm while rotating the airfoil in order to plot cl vs alpha graph etc do you how can i do that
I set my rotating interface as 170mm in diameter, and the boundary interface as 170.01mm diameter, why do i still having "contact region" in my mesh interface?
It seems the contact region was created automatically when starting Ansys Meshing. You can delete "Contact region" under "Connections" in the Meshing Window and then set up the interface manually.
Sorry, I don't know why. Ansys creates multiple contact wherever it thinks should be connected or is connected. And I think it depends on the geometry.
Sir I cannot express my gratitude towards You in plain words! You have helped me do one of the most critical simulations for my project. I will be crediting You and citing the video link in the future for my project! Thank You and please keep the good work going on!
Nice! You're welcome. Thank you for your supporting !
Hi, I really appreciate everything you post in your channel. You videos are very informative and I've learned a lot from them. I would like to ask if you can please to show me the required steps to draw the flowing grid H-O-H and J-grid mesh. Best Regards.
thankyou very importatnt topic
thank you so much!!
Good work i like it
Can this method be used to calculate lift, moment and drag coefficient of a dynamic aerofoil? I need to find the coefficient values for changing the angle of attacks and different pitching rates.
Hello sir, Did you receive the method to find those lift and drag coefficients for varying pitch rate and angle of attack as you asked
@HTC, sir, can you please make the same video using the 2022 version? It is essential, please make it early
Hello.
Thank you for the video.
I have a question. It is possible to put the moving circular zone in motion not with a constant value of 0.5 rad/s but using a UDF function which assign an angular velocity in function of time?
Thank you.
Hi, my airfoil is during calculation flying away and the airflow doesn't flow into "rotate", do you know what could be wrong? Thanks
Even I am facing the same problem
Same issue here. its just moving upwards in the y direction and not rotating
Hi, Thank you very much for this tutorial. But I tried to do this in 3D but I get a problem of negative cell in the calculation step. What you can advice?
How would I set up 2 airfoils next to each other and rotate both at once? By copying this method exactly the meshes overlap and cause errors
how the rotating speed is 0.5 rad/sec. even how to decide that value.
Depends on the angles of attack you want to sweep through. But this person set it up such that the time step was 0.005 sec, with 400 iterations. 0.005 sec*400= 2 sec. 0.5 rad/s * 2 sec= 1 rad. 1 rad = 57.2958 degrees.
I believe this is the logic.
Thanks sir, tutorial is great. Is there a way to print angle of attack at each iteration?
Thanks for the video sir .but while creating the fluid surface and rotating surface. I'm getting an error like" intersecting profile is not allowed" or sometimes "invalid profile selection"!! PL help me in this regard
How to calculate rotational velocity
love you
haha :P :D
I want to simulate a rotational 3d airfoil but I cant make different separate zones. would you please help me?
Hey bro, Sorry I am not asking related question... I want to simulate NACA 0012 and 0015 at stall angel in ansys fluent, Which models should I use and how refined mesh should be? Speed of air is 50m/s. Thanx in advance.
hey, I did a analysis on tapered wing, with NACA 23012. laminar model with 57 m/s velocity inlet. but the Cl values I get is in the range of 100..y is that.. is there any solution for it?
It is better to upload this rotating airfoil from ansys 2020 2r.
Is there a way to do this with 3D shapes?
yes, of course.
Hello sir
Can i find the noise generated form rotating aerofoil ..???
Hello Sir! Do you think it would be possible to share the mp3 video? I would like to use it to explain my students flow separation and pressure gradients with variations in AoA :D
Hello I did the analytical of a NACA 4415 in drag fluid and lifting the results these
Cl = 7.2870e-04 and Cd = 1.7649e-05
The experimental results are
Cl = 0.787785 Cd = 0.01218
I would like to know how to interpret these fluid values and whether they are correct or approximate with the experiments
did you check your reference values ?
How do you calculate relative velocity and Reynolds number?
it moves away instead of rotating.
Did you use Dynamic Mesh?
No, I used Sliding Mesh.
@@htc2930 Can it be done by overset mesh?
@@htc2930 excuse me sir, how to use this method on dynamics mesh or moving mesh please help me some advice. thank you very much if you reply me i'm a student.
Can you do a video on Bird flapping.
Can I ask how do I improve the quality of the video? its really blurry :(
How can I make 4 airfoil sliding mesh using designmodeler. Thanks
I don't understand what you mean ?
I want to analyse a four bladed dareius turbine using fluent. However, I want to know how to go by the geometrical drawing using ansys designmodeler or autocad. Any good link? Thanks
This in CATIA and Solidworks:
th-cam.com/video/GFyNCK2qrEs/w-d-xo.html
th-cam.com/video/GUkWRQc2QAY/w-d-xo.html
If you want to know how to create an airfoil in DesignModeler, check this:
th-cam.com/video/thrB-mKHGek/w-d-xo.html
Or send me your model's picture that you want to design.
Thanks for the replies. Can you further describe how you can make the airfoil into a four-airfoil sliding mesh pattern...using designmodeler. Thanks
bro i need the mesh file how c
an i get that?
Brother how can i obtain Cl vs angle of attack ? can i botain it from a rotating airfoil?
any luck?
@@ram5798 Monitors
Sir I'm getting a error like unassigned interface zone detected for interface 9 flow cannot be initialized, I can't initialize the flow
Try to change the mesh quality.
Thanks for the video, I need to model hot air flow past multiple porous bodies. Can anybody help me please
during meshing it gate stuck , i don't know why. could you give me any suggestion.
may be your meshing is very high resolution one so wait half an hour
Thank you for the excellent work! Can you simulate the wing's motion forced by the flow? Thank you!
You would need a detailed flight dynamics analysis for that.
thanks for the tutorial but i have a problem at 10:58 you edit the airfoil that is a wall but when i click edit for airfoil there are no options appear. I can't figure out why it is not showing me anything i check the mesh and named selections they look okay like you do.
Do you have opinion about whats causing it ?
There are some tabs in the new window, make sure that you have clicked on the Momentum tab.
I fixed something was wrong in my geomety nut now it is working fine. I actually want to calculate cl cd cm while rotating the airfoil in order to plot cl vs alpha graph etc do you how can i do that
what tunes
I set my rotating interface as 170mm in diameter, and the boundary interface as 170.01mm diameter, why do i still having "contact region" in my mesh interface?
It seems the contact region was created automatically when starting Ansys Meshing. You can delete "Contact region" under "Connections" in the Meshing Window and then set up the interface manually.
+HTC Why is there no "contact region" generated automatically in your model?
Sorry, I don't know why. Ansys creates multiple contact wherever it thinks should be connected or is connected. And I think it depends on the geometry.
Hey man, last question. How do you collect the rotating speed in fluent?
what exactly do you mean ?
SALSA
You can at least explain steps instead of that boring music.
bhai yar