Observations of the Flow Patterns of Two-Dimensional 4 per cent Thick Biconvex Aerofoil at M0= 1.40 and 1.63

摘要

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.nShock-induced boundary-layer separation at the trailing edge of the aerofoil was present at M0 =1-63 with transition free boundary layers but was absent upto 5 deg incidence at Mo = 1.63 withjgansitionzfixed boundary, layers and up to 6 deg incidence at M0 =1.40 with transition-free boundary layers.