Numerical Simulation of Large Angle-of-Attack Separated Flows Over Airfoils of HAWT Rotors

摘要

regulated HAWT rotors and constitute the base of the flutter estimation of blades. This paper presents a numerical simulation of large-angle-of-attack separated flows over airfoils for stall regulated HAWT rotors. The two dimensional Navier-Stokes equations in a body-fitted system is adopted, and the C-type grid system is generated, applying CAD surface structure technology and multi-block grid technology. The two-dimensional flow is modelled as turbulent and incompressible. Numerical solutions are obtained using the RANS scheme with a double equation model of RNGκ-ε. Numerical simulation of flow over FFA-W3- 211 airfoils is given, and the accuracy of the numerical results of lift and drag coefficients is compared with wind tunnel test data at angles of attack from -6° to 60°. The comparison between them shows good agreement.