[subham998]

I am trying to perform the simulation of a NACA0012 airfoil at a very low Reynolds number. The lift and drag coefficient matches exactly with the experimental data up to 5 degrees. However, for an Angle of Attack of 10 degrees and above, the simulation is over-predicting the lift coefficient. The drag coefficient is however within the error bars. One of the reasons might be the transition from laminar to the turbulent regime and successive reattachment, which gives rise to bubble separation and hence alters the lift and drag coefficient. How can I solve this problem?