NACA-RM-L54F25

Abstract

INTRODUCTION <br>Various investigations have been conducted that are concerned with the aerodynamic characteristics of the Douglas D-558-II research airplane which is currently undergoing flight tests by the NACA High-Speed Flight Research Station at Edwards Air Force Base, Calif. A 1/16-scale model of the original configuration has been investigated at high subsonic and low supersonic speeds in the Langley 8-foot high-speed tunnel (ref. 1) and at mach number of 1.61 and 2.01 in the Langley 4-by 4-foot supersonic pressure tunnel (refs. 2 and 3). Recently the original model has been modified to simulate more closely the present airplane configuration by the addition of a canopy and by increasing the size of the vertical tail. A small vane simulating that to be used in conjunction with a yaw damping system proposed by the stability Analysis Section of the Langley Aeronautical Laboratory (ref.4) was also incorporated into the model. <br>The present paper presents the aerodynamic characteristics of the revised model in pitch and sideslip, with and without a yaw-damper vane, at a mach number of 2.01 and a Reynolds number of 1.46 X 10 ⁶ based on the wing mean aerodynamic chord. The model was tested through an angle-of-attack range of about -2&#176; to about 13 at an angel of sideslip of 0&#176; and an angle-of-sideslip range of 2&#176; to about 10 at an angle of attack of 0&#176;. These results are compared with those obtained for the original model configuration.