[Arjun_kalkur]

Hey Im simulating a flow over an airfoil with flap with airfoil of chord 100mm, but the slot lip ends at 90% of chord and a fowler flap of 30mm chord is used.

I tried to create a better mesh, average skewness is 7.79e-02.
Although 5 cells are highly skewed.

I named main airfoil and flap separately.
I chose the reference area as 0.12m, (is it correct?) later i tried to solve with almost all possible turbulence model, but it diverges (epsilon, omega) and laminar model behaves quite smoothly till some point and then oscillates.

The inlet velocity chosen was 15m/s.

The continuity residual also increases with iterations.
I get the divergence in the early stage itself along with limit on turbulence viscosity and reversed flows.

I have a doubt that my mesh needs more layers on the airfoil.
I've attached the images, please have a look.

I've tried almost everything, please help ! Thanks alot

https://drive.google.com/file/d/0BzX...ew?usp=sharing

https://drive.google.com/file/d/0BzX...ew?usp=sharing