Abstract:
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 and 0.70. Pressure distributions and flow photographs are presented which illustrate the growth of the 'bubble' of separated flow.
