3D,analysis of NACA-0012,with WINGLET & non.
 

I need an analysys of NACA 0012 Airfoil(chord=1 unit & SPAN =8 x chord) one time without any winglet.other time with very thin winglet(NACA 0012) installed at 90,115,125,135,145 degree ANGLE to outbord(for example the shape is for 135 deg = _____________/ & for 90 deg = _____________| ). (span of winglet is 0.5 chord of wing).upstrem velocity is 200 m/s. the output needed Cl-Cd at angle of attack between 0 to 10 degree & contour of velocity & pressure change in 3D & 2D. I need to ploting result.... PLEASE HELP ME,I have only 2 days time. PLEASE,PLEASE WITH BEST REGARDS THANK YOU

17 sep 2006

meshing around the body and tip of NACA0012
 

I would like to know , how many layers of elelments should i use to capture the boundary layer and what type of elelment should i use at the tip Of NACA0012.

Re: meshing around the body and tip of NACA0012
 

Well, since you didn't mention if you need to calculate Compressible flow around NACA0012 or incompressible flow.

Anyways, I'll give you just a suitable guidelines for mesh generation around NACA0012.

Usually if you use SST K-W turbulence modle, it is advisable to use atleast 10 layers of prism with prism ratio between (1.25 ~ 1.5). In my experience, this gives better result for TETRA mesh.

In case, you plan to use HEX mesh, you should better make C-type grid at the LE and H-grid at the TE. And, for BL resolution, use almost the same ratio. Make sure that you meet the turbulence model guidelines for Y-plus value. In case of SST K-w model, you should ideally have Y-plus less than 1 (~5).

I hope this would help you solve your problem.

Good Luck and Best Regards, Imteyaz

Re: meshing around the body and tip of NACA0012 *NM*
 

Re: meshing around the body and tip of NACA0012
 

send me this information