Observations of the flow past a two-dimensional 4 per cent thick biconvex aerofoil at high subsonic speeds

Abstract

Flow photographs and detailed pressure distributions for a 4 per cent thick circular-arc biconvex aerofoil at high subsonic speeds and high incidences have been analysed and the divergence boundary (defining the onset of separation effects) for the aerofoil determined. Emphasis was placed on the transition from leading-edge to shock-induced separation as the free-stream Mach number was raised at a fixed incidence.