Pneumatic Yaw Control Effector for Aircraft Williams, David R. Seidel, Jürgen An apparatus and method for controlling a yaw moment of a flight vehicle, such as an aircraft. A wing structure of the flight vehicle has a first opening or actuator positioned by a first apex section of a first side of the wing, and has a second opening or actuator positioned away from or at a distance from a second apex section of a second side of the wing. The first side and the second side can each be positioned or located opposite a centerline of the wing or wing structure. A pressure source or other pressure supply device is in communication with the first opening or actuator and the second opening or actuator to which a pressurized fluid, such as air, is controlled and delivered to control or vary the yaw moment of the flight vehicle. Sponsorship: Illinois Institute of Technology United States Patent 2018-04-18 2018-04-17 Patent application/pdf islandora:9888 9,944,383 http://hdl.handle.net/10560/4253 en CC0 1.0 Universal http://creativecommons.org/publicdomain/zero/1.0/ No Copyright - United States http://rightsstatements.org/page/NoC-US/1.0/ Open Access