Hi, I KEEP GETTING AN ERROR OF ONE OR MORE ENTITIES FAILED TO MESH and the mesh generation did not complete due to poor-quality elements. please help and direct me further. Thank you.
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 ?
one year late but for whoever finds this, here is the solution: make sure the direction vector is pointing TOWARDS the surface where the edge will be projected. If the edge is below the surface, the vector has to point up. If the edge is above the surface, the vector must point down.
@htc i very thankful for this tutorial i am new in ansys cfx and i have why we use scale and minimize the airfoil what the point of this step and i can use different coordinate for draw the airfoil like first naca0015 cord. file and the second naca0012 coordinate file ???? :)
first of all the curve is not imported as closed loop . so i have to add a line to make it closed. and then the skin loft operation ... i'm stuck ! need help ...
nice tutorial but my infliation always fail i tried everthing i cant figure out why i used your setting my wing's chord length is 6cm i used 0.008cm total thickness and post infliation max layer of 5
Thanks. This tutorial is really helpful for my project. However, I have a question. I don't know why did you set up Velocity 100m/s.. Can i set up Velocity 232m/s ?
@HTC i know it's random..but i really need help with this, I can't get the projections right. It would be great if u could help me with my project as it's urgent
I'm a bit late but I'm doing something similar at the moment. Just extrude a box around the tubercles and boolean the tubercles from the box, then boolean the box from the domain (preserving tool bodies) Insert a patch conforming method for the 'tubercle box' and do everything else the same as in this video :) As an aside - you can get a structured mesh for your case if you wish, even in Ansys Meshing, but it's difficult & will require slicing the geometry into lots of different bodies.
i am having the same problem ! first of all the curve is not imported as closed loop . so i have to add a line to make it closed. and then the skin loft operation ....did u find the solution ...? i'm stuck !
This uses a wrong way of domain creation... Literally gives wrong values.. My simulation was running around 2 days and literally spoiled my system.. When tried the same simulation condition with rectangular domain took only 1 hr..
Hi, I KEEP GETTING AN ERROR OF ONE OR MORE ENTITIES FAILED TO MESH and the mesh generation did not complete due to poor-quality elements. please help and direct me further. Thank you.
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 ?
hi, is there any difference of drawing the boundary this way then making an uniform enclosure as the boundary?
im getting an incomplete projection error on one of the lines. Any help??
one year late but for whoever finds this, here is the solution: make sure the direction vector is pointing TOWARDS the surface where the edge will be projected. If the edge is below the surface, the vector has to point up. If the edge is above the surface, the vector must point down.
@htc i very thankful for this tutorial i am new in ansys cfx and i have why we use scale and minimize the airfoil what the point of this step and i can use different coordinate for draw the airfoil like first naca0015 cord. file and the second naca0012 coordinate file ???? :)
@HTC. Hey, I've a problem in selecting the face after revolving for extrusion of the flow domain. can you please help me ASAP.
first of all the curve is not imported as closed loop . so i have to add a line to make it closed. and then the skin loft operation ... i'm stuck ! need help ...
thank you for this useful video i had question about the angle of attack how i can enter the value of it in 3d solutions ?????? thank one more time :)
nice tutorial but my infliation always fail i tried everthing i cant figure out why i used your setting my wing's chord length is 6cm i used 0.008cm total thickness and post infliation max layer of 5
el archivo de coordenadas me sale error al leerlo, como lo ingresas en un documento de texto?
Thanks. This tutorial is really helpful for my project. However, I have a question. I don't know why did you set up Velocity 100m/s.. Can i set up Velocity 232m/s ?
why not ?
@HTC i know it's random..but i really need help with this, I can't get the projections right. It would be great if u could help me with my project as it's urgent
what did you mean "can't get the projections right"? plz describe your problem in more detail.
hi,
You can explain to me why we need more domain near the wing?
That is so you can specify a different element size within that region (closer to the wing) that is smaller than the global mesh settings.
can you please make a video on wings with tubercles?
I'm a bit late but I'm doing something similar at the moment.
Just extrude a box around the tubercles and boolean the tubercles from the box, then boolean the box from the domain (preserving tool bodies) Insert a patch conforming method for the 'tubercle box' and do everything else the same as in this video :)
As an aside - you can get a structured mesh for your case if you wish, even in Ansys Meshing, but it's difficult & will require slicing the geometry into lots of different bodies.
Everytime "Error: Self intersecting or invalid profiles
"Context: Extrude Feature Extrude1"
i am having the same problem !
first of all the curve is not imported as closed loop . so i have to add a line to make it closed. and then the skin loft operation ....did u find the solution ...? i'm stuck !
@@mithunmahato309 3 years later and we still without answer :(, i have the same problem in the loft dude
ATTACK ANGLE, WHERE DEFINED
I HAVEN'T WATCHED THE WHOLE SERIES BUT HE PROBABLY DEFINES IT IN THE VIDEO WHERE HE GOES OVER THE SOLUTION SETUP
check where hes inserting X and Y component of velocity. Actually its sin and cos of the AoA
This uses a wrong way of domain creation... Literally gives wrong values.. My simulation was running around 2 days and literally spoiled my system.. When tried the same simulation condition with rectangular domain took only 1 hr..