Abstract:
The 12.2% thick RAE 100 aerofoil section was chosen as being likely to fulfil the requirements for the basic aerofoil section of a series of swept-back wings designed to provide fundamental information on the high lift and stalling behaviour of swept wing aircraft. The choice was based upon previously published work on the stall characteristics of two-dimensional aerofoils, and the results presented show that the desired behaviour at high lift has been obtained. The measurements of the aerofoil characteristics were obtained by surface pressure plotting. Not only were the overall forces and moments obtained from these measurements, but also the pressure distributions were analysed in three ways intended to provide information on the changes from the potential flow pressure distribution which are produced by the displacement thickness of the boundary layer.
