Abstract:
Low-speed wind-tunnel tests have been made, under as near two-dimensional conditions as possible, on a wing section with plain leading- and trailing-edge flaps. The increases of lift resulting from boundary-layer control by blowing over the trailing-edge flap have been measured for a range of flap deflections, as has the effectiveness of a leading-edge flap for increasing the stalling incidence and maximum lift coefficient. Some comparisons with the predictions of inviscid theory have shown good agreement between predicted and measured pressure distributions, and suggest that minimum aerodynamic drag occurs when the inviscid lift is achieved.
