Previous studies involving flight testing of flap gap seals on a Piper Arrow II revealed a decreased maximum lift coefficient, and corresponding increase in stall speed. The purpose of this study was to examine the aerodynamics of a 3/16 scale, two-dimensional model of the Arrow wing in a more controlled environment of a wind tunnel. The study concentrated on maximum lift, but also addressed drag and other aerodynamic parameters. Tests were conducted at Reynolds numbers of 600,000 and 900,000, with flap deflections set at 0, 10, 25 and 40 degrees, corresponding to those of the full-scale aircraft, and angle of attack varied from -4 deg to 16 deg. Although no clear trends in drag reduction were indicated, the results showed a consistent decrease in maximum lift coefficient with the seals installed as opposed to the normal configuration.
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