Abstract:
Part I compares the experimentally determined aerodynamic characteristics of two 10½% thick supercritical aerofoil sections, RAE(NPL)9515 and 9530, over the Mach number range 0.3 to 0.88 and angles of incidence from -0.82° to 14°. The results are compared with the limited published results for aerofoils of a similar type. Part II presents corresponding results for RAE 9550, a 12.2% thick super- critical aerofoil derived from an NLR shockless lifting aerofoil, tested over the Mach number range 0.4 to 0.82 and angles of incidence from 1° to 11°. The results are compared with theory and with the limited published results for an aerofoil of a similar type.
