Subsonic Aerodynamic Characteristics of a Circular Body Earth-to-Orbit Vehicle

trim for a wide range of angle of attack. The maximum trimmed lift-drag (L/D) ratio for the aft center-fin configuration was less than 5, whereas the other configurations had values above 6. The aft center-fin configuration was directionally stable for all angles of attack tested. The wingtip and nose fins were not intended to produce directional stability, and did not. The rudder-like surfaces (controllers) on the wingtip fins and the all-moveable nose fin were designed as active controls to produce artificial directional stability. These controls were effective in producing yawing moment. Small rolling-moment values resulted from yaw control of the nose fin. Large adverse rolling-moment increments resulted from wingtip-fin controller deflection above an angle of attack of 13°. Flow visualization indicated that this was most likely caused by the influence of wingtip-fin controller deflection on wing flow separation. Introduction The N