WINGD-TUNNEL INVESTIGATION OF AN NACA 0009 AIRFOIL WITH 0.25- AND 0.50-AIRFOIL-CHORD PLAIN FLAPS TESTED INDEPENDENTLY AND IN COMBINATION

摘要

Wind-tunnel tests have been made to determine the aerodynamic section characteristics of an NACA 0009 airfoil with plain flaps 25 and 50 percent of the airfoil chord. The flaps were tested independently and in combination.nResults of the investigation indicated that the larger flap would provide greater lift increments but would lose lift effectiveness at the higher-deflections, and at a lower angle of attack than would the smaller flap. The hinge-moment and lift-effectiveness parameters for each flap indicated good agreement with curves predicting the, variation of these parameters with flap chord.