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Wind-Tunnel Investigation of an NACA 23012 Airfoil with an 18.05-Percent-Chord Maxwell Slat and with Trailing Edge Flaps
NATIONAL AERONAUTICS AND SPACE ADMIN LANGLEY RESEARCH CENTER HAMPTON VA
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An investigation was made to determine the optimum slot gap of he Maxwell slat for and the aerodynamic section characteristics, of the NACA 23012 airfoil with several deflections of a slotted and a split flap. It was found that, for he combinations tested, a slot gap of 0.0175 c was the optimum. This gap appreciably increased the maximum lift coefficient and angle of attack at the stall. The effectiveness of the slat, however, dropped with increasing flap deflection.
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