A MEAN CAMBRLINE SINGULATITY METHOD FOR TWO-DIMENSIONAL STEADY AND OSCILLATORY AEROFOILS AND CONTROL SURFACES IN INVISCID INCOMPRESSIBLE FLOW

摘要

A numerical method has been developed to calculate the pressure distribution on the surface of steady and oscillating aerofoils in incompressible inviscid flow. In this method singularities are placed on the mean camber line of the aerofoil and the boundary condition of tangency of flow is satisfied on the surface of the aerofoil. Problems considered include steady single aerofoils with and without control surfaces, a cascade of aerofoils, aerofoils oscillating in pitch, aerofoils oscillating in heave, aerofoils in harmonic travelling gusts and control surface oscillations. Comparison with analytic solutions, and other numerical methods, where available are good. The main advantages of this method are the relatively fast computing times and the fact that the method converges satisfactorily in the limit of zero aerofoil thickness.