The laminar boundary layer on a rotating wind turbine blade

The present paper describes a method to calculate velocity profiles in the boundary layer ofrotating blade. A differential approach is used to solve the laminar boundary layer equations. Theeffects of tip speed ratio, dimensionless radial position r/R and angle of attack have been analyzed.The test airfoils used in the simulations are NACA 63-215 and S809. The resulting velocity profiles inthe chordwise and spanwise directions are mapped and stored in a Database according to theboundary layer parameters

Transonic Airfoil Flow Simulation. Part II: Inviscid-Viscous Coupling Scheme

A calculation method for the subsonic and transonic viscous flow over airfoil using the displacement surface concept is described. This modelling technique uses a finite volume method for the time-dependent Euler equations and laminar and turbulent boundary-layer integral methods. In additional special models for transition, laminar or turbulent separation bubbles and trailing edge treatment have been selected. However, the flow is limited to small parts of trailing edge-type separation. Comparisons with experimental data and other methods are shown