Subsonic Force Characteristics of a Low Aspect Ratio Wing Incorporating a Spinning Cylinder.
NAVAL SHIP RESEARCH AND DEVELOPMENT CENTER BETHESDA MD AVIATION AND SURFACE EFFECTS DEPT
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The effect of a spinning cylinder on the aerodynamics of a low aspect ratio wing was examined in a subsonic wind tunnel program. Results show little effect with the cylinder in the wing leading edge for a velocity parameter of 5 and flow angles relative to the wing up to 16 degrees. However, similar flow conditions with the cylinder relocated to the trailing edge, produce a doubling in the force coefficient. An undeflected flap added to the trailing edge cylinder model nullifies the cylinders effect. With the flap deflected 30 degrees, large increases in the force coefficient occurred at moderate sideslip angles.