In order to reduce the frictional drag of the aerofoil it is desirable that the flow in the boundary layer retains laminar as possible along the surface. As the increasing pressure gradient is a cause of early transition from laminar to turbulent flow, it is necessary to make small the increasing pressure gradient along the surface. For this purpose the point of the maximum thickness of the aerofoil section must be shifted suitably backward. In the present paper the symmetrical aerofoil sections of such kinds were designed by the method of sources and sinks and the aerofoils with nearly uniform pressure distribution were obtained.
Design of Symmetrical Aerofoil Sections Suitable for High Speeds.
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