Wing Geometry Problem
 

I am trying to mesh a simple rectangular wing in the ICEM CFD. I have made the geometry in Solid Works and imported the step and iges files in the ICEM CFD for meshing but the surface on the Trailing Edge of the wing is not exactly following the rounded contour of the curves, so i am getting the bad tetra and prism mesh in this region. Pictures are attached for the reference. Please check the attachments for the figures. Kindly help me in sloving this issure. I am really stuck up in this.

send me ur geometry . I'll try.

Hi cfd seeker,

As far as I see it, you have a few possible solutions. Tetrahedral (and any FE cell for that matter) all have straight edges. In order to accurately capture the curvature of your wing profile, you will have to refine the area. By creating a density box, you can increase the local refinement. Also by splitting surfaces where curvature is greater than ~30 degrees, you can create more curves on the surface for nodes to "stick" to (using patch conforming method).

If this is an airfoil TE, however, do you really need to capture that curvature? A non-sharp TE is going to destroy alot of your airfoils efficiency! By not satisfying the Kutta Condition, you are allowing circulation at the TE and therefore allowing the rear stagnation point to migrate away from the geometrical TE (== loss in lift)

try curve meshing set-up. assign appropriate nodes and bunching law.

Thanks a lot Ali and Stuart for your ideas. Actually I have a separate surface for the wing tip, separate surface for the rounded trailing edge and yet another separate surface for the the rest of the wing and curves of the tip surface and curves of the rounded trailing edge are coinciding with each other and I am totally confuse how to go about it. As far as you are talking about splitting the surface or curves then I really don't know about this as I am totally new on ICEM, kindly help me in this?

Stuart you are talking about the sharp and rounded trailing edge, I have read somewhere that real wings can't be made sharp in any case, so there is always a small radius at the trailing edge but you are saying that there is a loss of lift because of the rounded trailing edge?? Please clarify this point also?

Does any one of know how to generate the structured quad/hexa mesh on this geometry?

do you also have hexa licence? if so, it's very easy to generate a good quality mesh in case of this easy geometry.

do you have any experience with icem hexa yet?

Energy mu university has the license for that and no i don't have have any experience for the quad/hexa mesh yet....can you please help me for this???

if you provide the .tin file, i'll take a look on it

Yes Energy kindly tell me your email id, i will mail you the tin file of my wing or tell me your id through private message. thanks
Regards

share and send link
 

share the file on any file sharing site (I use www.4shared.com) and send link through pm or on forum. Forum sharing is better option as others may be able to help you out.

Far I have told the problem in the other topic. My geometry is at my workplace but its a simple rectangular wing made of Naca 0015 airfoil, 1,7 feet chord and 5.59 feet semi-span, I only want to analyze the semi-span without fuselage...

Please reply here Far, Simon, Stuart....