Wind-tunnel tests on the NACA 63A009 aerofoil with distributed suction over the nose

Abstract

Preliminary wind-tunnel investigations into the effectiveness of distributed suction over the nose of a thin aerofoil in delaying the stall, and in increasing the maximum lift coefficient have been carried out in this country by Pankhurst, Raymer and Devereux (1948) on HSA V (NPL 308) aerofoil and in America by Nuber and Needham (1948) on NACA 64A212 aerofoil. The present experiments were undertaken to add to the available knowledge by testing another section. In particular, information was sought on scale effect on suction quantity, on the effect of distributed suction on a flapped aerofoil and on the influence of the shape of the nose of the section on the maximum lift coefficient obtainable with suction.