The development of leading-edge flow separation as incidence is raised, for a 4 per cent thick twodimensional biconvex aerofoil, was studied experimentally for wide ranges of incidence at Mach numbers of 0.40, 0.50, 0.60 ...

Flow photographs and detailed pressure distributions for a 4 per cent thick circular-arc biconvex aerofoil at transonic speeds are presented. The results for incidences of 0, 1, 2 and 5 deg are analysed in detail.

Direct-shadow and schlieren photographs and pressure distributions of the flow past a two-dimensional 4 per cent thick biconvex aerofoil for a limited range of incidences at Mach numbers of 1.40 and 1.63 are presented. ...