I think you should use k-omega SST, rather than k-epsilon, as k-epsilon is not very accurate in adverse pressure gradients, so not viable for aerofoils. It might not show a problem here, but at higher angle of attack it will not simulate the flow correctly, as it does not show flow separation. You could also see that you lift and drag coefficients were really wrong, they usually have values around 0-2 for Cl and like 0.015 or so for Cd, definitely not 6000. You should also do mesh refinements rather than making the whole area really fine mesh.
Thank you for this! This will help me with my third year project on studying suction and blowing flow control on an aerofoil and how it affects aerodynamics :)
You will likely have to zoom in on the trailing edge and connect the two points at the very end with a short line. This should fix your continuity issues
Why would the fluid flow be normal to boundary? Should it not have an X component instead, as being normal to boundary will disrupt a free-flow condition?
good video, i am having some doubts . for this case i want to write a coefficient of moment also for the different angle of attack. what are the moments points and moment axis i should consider. and for also 3d cases similar like this one i wanna know about the co eff- moment . kindly explain me .
Brother the coordinates imported always have the tail area open (upper region not joined with the lower one) so I can’t generate surface from edges as can’t get edges joints generated.
I’ve had that happen to me a few times as well. The gaps have been very narrow in my experience so I’ll usually make a line to connect the two rail points and complete the surface. Since the gap is narrow, the line rarely hurts the simulation (it’s actually more accurate to manufactured wings since they almost always have a thin flat end at the back of the airfoil). If you need a very fine tip, you can also alter the coordinate for one of the tips so that they join together. Hope one of those works!
If you're in setup go to Results -> Create (under Surface) -> Zone -> surface-body (on left) -> create it will show up. I had trouble getting it to work too.
In sketch mode you should be able to zoom in on the trailing edge corner (where the point is missing) and draw a line to connect the two points that are present. Once you do this, you will be able to crate a line from the sketch, then a surface from that line and the line created from the coordinate file.
Good video about CFD, but your explanation about the lower pressuere on the top of the airfoil (19:40) is wrong, the igual transit time "theory" is wrong because don't exist any type of physical principle that implie that the air on the top must reach the end of the airfoil at the same time that the air on the bottom, in fact if you analyses a wind tunel experiment you will see that the air on the top reach the end of the airfoil before the air on the bottom what proof that your explanaton is wrong. ruclips.net/video/UqBmdZ-BNig/видео.htmlsi=ZWkgGfPqWnOamMJH Here is a video of a wind tunel.
Hey, After I have given Initialize in the hybrid initialization, it says "WARNING: unassigned interface zone detected for contact_region-trg" and Unassigned interface zones found. Flow is not initialized. Any help would be much appreciated. Really need it.
How can you feed people with this s***t being so confident? An impressive skill. 6000 Cd? For real?! List of critical mistakes: -shitty mesh without inflation layer around the foil; -wrong turbulence model absolluetly; -no reference values have been set for propper coefficient calculation. My suggestion, delete this, fix mistakes, upload again. It is an anti tutorial, harmful one.
![[TF2] The Russian Bear Trap](http://i.ytimg.com/vi/YFNSwz2_rOA/mqdefault.jpg)
When I see the inlet velocity directed Normal to the Boundary, my eyesore came back.
This is the best airfoil fluent video i ever seen..great job
Thank you!
I think you should use k-omega SST, rather than k-epsilon, as k-epsilon is not very accurate in adverse pressure gradients, so not viable for aerofoils. It might not show a problem here, but at higher angle of attack it will not simulate the flow correctly, as it does not show flow separation. You could also see that you lift and drag coefficients were really wrong, they usually have values around 0-2 for Cl and like 0.015 or so for Cd, definitely not 6000. You should also do mesh refinements rather than making the whole area really fine mesh.
hi bro. i am ur 100th subscriber. ur video helped me a lot in my project review. i am so grateful to u. love from INDIA.
Thank you for subscribing! I’m glad I could help. Much love to India!
Cheers for this solid video, really comprehensive, helped me a lot when my usual method kept crashing :')
Thank you! Always happy to help!
thank you so much for this!! first time using ANSYS and i needed to model a glider, this was a great start!
Great video man. This really helped me to get on my foot on Fluent and ace my CFD project. God bless u!
Always happy to help!
Thank you for this! This will help me with my third year project on studying suction and blowing flow control on an aerofoil and how it affects aerodynamics :)
Happy to help!
Hey I'm doing the same.
Mind filling me on the details?
My lift and drag coefficients are in the millions
Why is the Cl coefficient so high?
what to do if its showing "Edge joints generated" as 0???
I keep getting an error about bottom curve coordinates I can’t create a curve area my bottom curve isn’t intersect the origin PLEASE HELP
You will likely have to zoom in on the trailing edge and connect the two points at the very end with a short line. This should fix your continuity issues
Why would the fluid flow be normal to boundary? Should it not have an X component instead, as being normal to boundary will disrupt a free-flow condition?
Unassigned interface zone detected for interface contact region,,,, how i can solve this issue during intialization it happens
Hi.Can this ansys fluent give the optimized airfoil (optimied by ansys fluent itself) so i can have a excel file to import it to catia to 3D printing?
Thank you so much!
good video, i am having some doubts . for this case i want to write a coefficient of moment also for the different angle of attack. what are the moments points and moment axis i should consider. and for also 3d cases similar like this one i wanna know about the co eff- moment . kindly explain me .
Many thanks to you
Brother the coordinates imported always have the tail area open (upper region not joined with the lower one) so I can’t generate surface from edges as can’t get edges joints generated.
I’ve had that happen to me a few times as well. The gaps have been very narrow in my experience so I’ll usually make a line to connect the two rail points and complete the surface. Since the gap is narrow, the line rarely hurts the simulation (it’s actually more accurate to manufactured wings since they almost always have a thin flat end at the back of the airfoil). If you need a very fine tip, you can also alter the coordinate for one of the tips so that they join together. Hope one of those works!
@@dormroomengineering8689 hi how do you draw this line connecting the two points?
@Dorm Room Engineering nvm I figured it out
@@Onepiecefan609 Can you tell how?
I'm having the same problem
@@HameezAqeel edit your coordinate system so that it connects the dots.
Hey in contour plot , I dont see surface_body , i see only inlet, outlet, interior surf body, wall surface body.
pls help
If you're in setup go to Results -> Create (under Surface) -> Zone -> surface-body (on left) -> create it will show up. I had trouble getting it to work too.
I am not able to make a surface out of the sketches as the last pointis missing from the coordinates from the site itself...
What should I do?
In sketch mode you should be able to zoom in on the trailing edge corner (where the point is missing) and draw a line to connect the two points that are present. Once you do this, you will be able to crate a line from the sketch, then a surface from that line and the line created from the coordinate file.
@@dormroomengineering8689 Thanks a lot, though I have proceeded with it already and was curious, on how you proceeded without the need of doing it...
How can we select the two edges
Ctrl+click, or cmnd+click for mac
Hey why is the Cl and Cd so high? Are we messing with the units?
Part of that is due to the increased angle of attack. Also, I believe my model was in inches
Yeah, hes just messing with this video. LOL. But a good introduction to airfoil simulation though.
Good video about CFD, but your explanation about the lower pressuere on the top of the airfoil (19:40) is wrong, the igual transit time "theory" is wrong because don't exist any type of physical principle that implie that the air on the top must reach the end of the airfoil at the same time that the air on the bottom, in fact if you analyses a wind tunel experiment you will see that the air on the top reach the end of the airfoil before the air on the bottom what proof that your explanaton is wrong.
ruclips.net/video/UqBmdZ-BNig/видео.htmlsi=ZWkgGfPqWnOamMJH Here is a video of a wind tunel.
Hey, After I have given Initialize in the hybrid initialization, it says "WARNING: unassigned interface zone detected for contact_region-trg" and
Unassigned interface zones found. Flow is not initialized.
Any help would be much appreciated. Really need it.
When making the geometry, after importing the coordinate file, did you draw a line to connect the points at the back of the airfoil?
@@dormroomengineering8689 actually I solved the issue. I didn't mesh it properly. Thankyou anyways😁
I am got the same issue,, how u solve that issue
@@sudarshanjagannathan4864 i got the same issue,, how u solve this
@@dormroomengineering8689 bro i got same issue can u help me
How can you feed people with this s***t being so confident? An impressive skill. 6000 Cd? For real?! List of critical mistakes: -shitty mesh without inflation layer around the foil; -wrong turbulence model absolluetly; -no reference values have been set for propper coefficient calculation. My suggestion, delete this, fix mistakes, upload again. It is an anti tutorial, harmful one.