NACA-RM-L50J20

Abstract

INTRODUCTION <br>Lateral-control devices &Signed for airplanes flying at high speeds may produce unsatisfactory lateral characteristics at the lower flight speeds. Much research has been made t o investigate the lateral characteristics of swept and -wept wings and low-aspect-ratio and high-aspect ratio wings equipped with several types of lateral-control devices (references 1 to 4 and unpublished results). In order to supplement further the data of the above references, an investigation has been made at a high Reynolds number in the Langley fill-scale tunnel on a 47.5&#176; sweptback wing having an aspect ratio of 3.4 and a taper ratio of 0.51. <br>The data presented herein include test results of a 19-percent-chord plain-flap aileron having various spans and trailing-edge thicknesses. The effects of spoiler spanwise and chordwise location and projection on the lateral characteristics of the model are also shown. The results are presented for the basic wing and the wing with extensible leading-edge and plain trailing-edge flaps through a range of angles of attack from small negative angles through maximum lift at a Reynolds number of approximately 4.4. X 10⁶ and a Mach number of 0.07.