Following the law of stress adopted in the Navier-Stoke a equations, the configuration of the viscous flow in planes at right angles to the axis of an infinite cylinder is found to be independent of the axial motion of the cylinder. In the limiting;case of a yawed or swept wing of very high aspect ratio, certain boundary-layer and separation phenomena are thus determined independently by the crosswise component of velocity. It follows that the effect of sweopback is to increase the area of stable laminar flow and to decrease the lift coefficient at which flow separation occurs.
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