Wind-tunnel tests were conducted at a Mach number of 4.04-to determine the effects of leading-ease sweep, angle of attack, and leading-edge thickness on thundery-layer transition on flat-plate wings. In addition, some results were obtained on wings having rounded leading edges. The transition point was determined for angles of attack up to 20° and for leading-edge sweep angles from 0° to 720 by the luminescent-lacquer technique of boundary-layer visualization.nThe data showed that transition always occurred along a front parallel to the wing leading edge, and that increasing the leading-edge sweep angle or increasing the angle of attack between the undisturbed stream and model surface caused the transition line to move closer to the wing leading edge and, in general, decreased the transition Reynolds number.
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