A mathematical analysis is made of the pressures produced on a general two-dimensional supersonic airfoil when the boundary layer is laminar, with especial note being paid to the realistic part played by Separation phenomena in altering drastically the flow over the entire-aft end of the profile, in contradistinction to what is premised when the boundary layer is turbulent. Moment changes can be of the order of 30 per cent between free-flight with an untripped boundary layer, and what might be measured in a high-speed tunnel having a turbulent stream; similarly, lifts might easily be reduced by 10 percent.
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