Experimental and numerical study on dynamic stall under a large Reynolds number

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 Reynolds-averaged Navier-Stokes (URANS) equation. And time-frequency characteristics were wavelet analysis. study showed that aerodynamic during dominated shear layer vortex (SLV) leading edge (LEV), phase difference between SLV LEV key factor existence bimodal force/moment. There linear correlation negative peak vortex-induced C p n this paper. During convection near-wall to trailing edge, high-frequency features firstly decay, multi-scale structures become more as gradually increases.