Aerodynamic characteristics of a single, stationary wing, whose tip is in an end-wall boundary layer, are studied experimentally to determine the effects of aspect ratio, tip clearance, angle of attack and end-wall boundary layer. Spanwise distributions of the lift and drag coefficient are derived and interpreted from the data obtained by chordwise pressure measurements on the wing surface. The results indicate that the slope of the lift curve, the angle of zero lift and the drag coefficient reach a maximum at an optimum value of the tip clearance in a certain range of the aspect ratio. Interesting information is also obtained for effects of the end-wall boundary layer on the lift and drag of the wing with a slot.

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