Investigation of Boundary Layer Transition on a Wing Profile at Supersonic Speeds,
FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OHIO
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The work is devoted to a study of the phenomenon of boundary layer transition on a parabolic wing profile. Particular attention is paid to an investigation of the effect of blunting of the wings leading edge as well as the effect of a single Re number on the transition of a laminar boundary layer to a turbulent one. An attempt was made to explain the reason for the influence of the degree of blunting of the leading edge on the transition region.