[otubaba]

Hi Guy,

I am running a 2D simulation on a NACA 0018 airfoil (Spalart Allmaras) , and I am having problem setting up the right Reference values to calculate the lift and drag coefficients. So far, my lift coefficient is lower than that of my experiment and other published works.

Here the values from my experimental set up:

Chord=0.25m, Span=0.3m, velocity=15m/s, AoA=10deg, air density=1.16kg/m3, viscosity=1.89541e-5kg/m-s

I'll be very grateful if anyone can help me solve this problem.

Thanks