Abstract:
Rotor blade aerodynamics are significantly influenced by dynamic stall. The objective of this study is to use a combined experimental/ computational approach toward better understanding of the dynamic stall phenomenon on the SC1094R8 airfoil. This study is part of a larger effort to alleviate the adverse effects of dynamic stall on rotor blade aerodynamics through airfoil shape optimization. In order to accomplish this goal, time-accurate surface pressure measurements along with lift and moment coefficients are gathered experimentally. Boundary layer tripping is performed to ensure behavior similar to that of the airfoil at larger Reynolds numbers. Sensitivity of dynamic stall under different flow conditions is also studied. Numerical simulations have been performed for similar flow conditions and compared with the experimental results. The result have aided in clarifying the sensitivity of dynamic stall as well as providing encouraging indications of the ability of the simulations to capture the important features associated with dynamic stall.