A Numerical Solution for a Steady Two-Dimensional Aerofoil with Control Surface in Incompressible Viscous Flow

摘要

A numerical method has been developed to calculate the pressure distribution on the surface of a two-dimensional aerofoil of arbitrary shape in incompressible flow, taking boundary layer effects into account. The method is a combination of the A.M.O. Smith technique for the estimation of the inviscid field with the Thwaites (laminar) and Horton (turbulent) techniques for the estimation of the boundary layer effects. The shape of the wake displacement thickness aft of the trailing edge is assumed; it is shown that the form of the wake displacement profile is not an important parameter. The method has been applied to aerofoils fitted with control surfaces; there are substantial differences between the theoretical results and experimental values which are attributed to the effects of gaps between the main aerofoil and the control surface.