Suction on airfoil boundary!!
 

Hi,
I'm trying to model a perpendicular suction outlet at 10% chord on a NACA 0012 airfoil.
I have created the mesh in ICEM and imported into fluent. It is an incompressible flow situation with a mach number of 0.3. I am using SST and using a boundary condition of velocity inlet, normal to boundary with a negative velocity of half free stream velocity (around -22.5m/s)
The results for this mesh with no suction inlet are pretty good at low angles of attack in terms of cl and cd close to experimental data but with this suction applied they just go totally astray. I've tried a number of times and mainly they both go negative or ridcliously huge values.

This is for a university final year project so if anyone could help me with what I could be doing wrong I would really appreciate it, I also want to demonstrate blowing in the same slot so if you could tell me what is the best boundary condition for that too it would really help.

Thanks :) :)

Hi Helena,

Can you explain a bit more about how to model the boundary layer suction problem? I am currently trying to simulate it.
Your suggestion will be valuable.
Please spend some time to share your experience.
Thanks in advance.