Evaluation of the Wright 1902 glider using full-scale wind-tunnel data

A reproduction of the Wright 1902 glider was wind-tunnel tested at the NASA Langley Research Center Full-Scale Tunnel through a range of conditions similar to those experienced 102 years ago. Data were collected over a range of angle of attack from -4 to 20 deg, and a range of sideslip angles from -20 to 20 deg. Both the canard and wing warp controls were actuated to determine control power, and a canard-only test was performed to augment estimates of pitch control power. An optimal lift/drag of 7.4:1 in ground effect was determined, comparing favorably with the Wrights' observations. This aircraft displayed levels of longitudinal and lateral control power that allowed, for the first time, control of an aircraft without reliance on weight shift. Because of its low pitch inertia and damping, the aircraft is sensitive in pitch and requires constant pilot attention to maintain an attitude. Laterally, the aircraft shows adequate roll rate and turn coordination, although a moderate sideslip will develop in turning maneuvers due to the lack of vertical surface area. Validation of the handling characteristics was aided through the use of a six-degree-of-freedom, commercially available flight simulator.