The bell-spanload, or bell-shaped lift distribution, gives proverse yaw for outer aileron deflections, a key factor in controlling a tailless vehicle. Study of bell-spanload applications have been limited to swept wings with elevon control schemes, relying on a well-tuned proverse yaw response for a differential elevon deflection. In examining unswept wings, symmetric outer control surface deflections have minimal associated pitching moment, allowing their use in adjusting the lift distribution to optimize for a wide range of flight conditions. Lateral-directional control of bell-spanloads can be improved by the use of an additional set of ailerons inboard of the mid-span vortices. The inboard ailerons provide traditional adverse yaw which serves as a linearly independent control vector relative to the existing proverse yaw outer surfaces; the two vectors are sufficient to define a parallelogram-shaped controllable region in the roll-yaw control space.

Document Type

Final Report

Author's School

McKelvey School of Engineering

Author's Department

Mechanical Engineering and Materials Science

Class Name

Mechanical Engineering and Material Sciences Independent Study

Date of Submission