Results: pressure computation from PIV measurements

A PIV database has been analyzed employing the proposed methodology. Among all the configurations analysed, we present here just the results for  the unsteady case with angle of attack α = 10°, downstroke, with  reference to the leading edge measurement window for brevity. The computed pressure field and the comparison between the computed and measured pressure coefficient are represented in the following figures. As it can be appreciated, the accordance between the computed and the  measured pressure coefficient is very good taking into account the fact that  the pressure is computed on points which are not on the airfoil surface but where the velocity vector is provided by the PIV measurements. Better results can be obtained through a suitable pressure extrapolation near the leading edge of the airfoil where the maximum discrepancy is observed since the flow exhibits a strong pressure gradient normal to the surface.