NACA-RM-A51A16

Abstract

INTRODUCTION <br>The X-3 airplane, designed as a supersonic research airplane incorporating Such features as a thin low-aspect&#8212;ratio wing and a large fuselage, might be expected to present stability problems in low-speed flight. The low-speed longitudinal characteristics as measured with a 0.16-scale model are presented in reference 1. References 2, 3, and 4 present the aerodynamic characteristics of the same model of the X-3 airplane at high subsonic speeds as measured in the Ames 16-foot high-speed wind tunnel. Since the construction and testing of the model referred to herein and in references 1, 2, 3, and 4, the design of the fuselage, wing, and empennage have been modified. <br>In conjunction with the determination of the low-speed longitudinal characteristics (reference 1) the lateral and directional stability and control characteristics of the model were determined and are presented in the present report. The data indicate the effects of the component parts of the model on the static lateral and directional stability and show the control effectiveness of the ailerons and rudder. During the investigation, large erratic rolling moments were encountered near the stall. These rolling moments were investigated in some detail and the results are presented herein. <br>The tests were conducted in the Ames 7-by 10-foot wind tunnel.