An axially symmetric analogue for general three-dimensional boundary layers

Abstract

On the assumption that the/tow normal to the external streamlines is small compared with that along the external streamlines it is shown that the streamwise momentum equation, the energy equation and the equation of continuity reduce to equations identical with those for flow over an axisymmetrical body, whose radius is determined from the local external flow. By solving these equations it is possible to obtain approximate values for the skin friction and the displacement surface in the case of wings at small angles of incidence, having no separations except at the edges. The theory applies directly for laminar compressible or incompressible flow, and the suggestion is made that it may apply also for turbulent flow.