NACA-RM-L8L29

Abstract

INTRODUCTION <br>The advantages of low-aspect-ratio pointed wings for high-speed flight have been outlined by Jones in reference 1. Extensive theoretical investigations of the stability characteristics of triangular wings have been made in the supersonic speed range. Theoretical investigations in the subsonic speed range, however, are very limited. The theory of reference 2 is considered to be applicable only to thin triangular wings of aspect ratios less than 0.5 and the theory of references 3 and 4 presents only a few of the stability characteristics. The approximate theory of swept wings presented in reference 5 might be expected to be unreliable as the taper ratio decreases from unity. <br>The present investigation was conducted to determine experimentally the effects of changes in profile and aspect ratio on the low-speed static-stability and rolling characteristics of triangular wings. The investigation was extended to determine the effects of adding fins to the upper surface and of cutting portions from the tips of a triangular wing to form low-aspect ratio tapered wings. Rolling characteristics were determined by means of the rolling-flow equipment of the Langley stability tunnel. (See reference 6) The experimental data are compared with available theory.