Abstract Dynamic stall under large Reynolds numbers and reduced frequencies has a significant effect on the performance of wind turbine blades, helicopter rotors, etc. So dynamic physics NACA0012 airfoil number Re = 1.5 × 10 6 was studied using experimental numerical methods. The frequency range k 0.035 – 0.1. unsteady flow field in detail by transient pressure measurement simulation based Reyn...

The large reverse flow region of the rotor with a high advance ratio is an important factor that affects performance improvement helicopters. This paper examines dynamic stall airfoil in to develop set pressure measurement systems for low region. pitch oscillation experiment NACA0018 and out has been carried out, influence motion parameters on stalls studied. results show more likely under stat...