[saylilyas]

Hello,
I am analyzing NACA0012 wing profile at low Reynolds Numbers.(135000). I must do this with pressure far field and velocity inlet-pressure outlet. However I got good result with pressure far field boundary type (very close to experimental values) by using k w SST turbulence model but unfortunately I could not get accurete results via using velocity inlet-pressure outlet boundary types. I only changed boundary types in GAMBIT. The mesh structure,velocity values, turbulence values turbulence model gauge and operating pressures same.
I always get lower value of coefficient of lift drag and pressure (more than 40% lower of the experimental value)
If you have any idea please help me.