Abstract:
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. Shock-induced boundary-layer separation at the trailing edge of the aerofoil was present at M 0 = 1.63 with transition-free boundary layers but was absent up to 5 deg incidence at M 0 = 1.68 with transition-fixed boundary layers and up to 6 deg incidence at M 0 = 1.40 with transition-free boundary layers.
