NACA-RM-A7L16

Abstract

INTRODUCTION <br>One of the major problems involved in the use of swept wings is the provision of adequate lateral control, especially at high lift coefficients. The experimental data of reference I indicate that the effectiveness of conventional ailerons in producing rolling moments is considerably reduced by incorporating sweepback in the wing plan form. Therefore, the effectiveness of a different type of lateral-control device, consisting of the rearward extension of the wing chord, was investigated on 45&#176; sweptback semispan wing. Spoilers were also tested on the same wing to determine the effect of spoiler location relative to the air stream on their effectiveness for providing rolling moments. <br>As simple sweep theory indicates that the damping in roll is reduced by sweep and, since it was believed that the chord-extension controls would increase this damping, comparative measurements were made of the rates of roll produced by these controls and by conventional ailerons on a full-span model of the same plan form as the semispan wing. In order to obtain a more comprehensive comparison of measured at various angles of yaw. <br>In an attempt to control the outboard spanwise flow in the boundary layer and thereby delay separation at the wing tip, the effect of fences alined in the free-stream direction on the upper surface of the semispan model was determined.