An active variable camber continuous trailing edge flapped wing wind tunnel model for aeroelastic “in-flight” shape optimization tests

The University of Washington designed and fabricated an aeroelastically scaled wing model for low-speed wind tunnel tests of real-time optimization-based continuous camber and twist shaping concepts for the SSCI DIRECT project. The model has twelve independently controlled trailing edge control surfaces. It was designed for the University of Washington’s Kirsten Wind Tunnel. Development of the model followed the successful development and wind tunnel tests of smaller earlier VCCTEF configured aeroelastic models for tests in which setting of the angles of the individual trailing edge segments was performed by hand. One of the major challenges with the new active model was to “package” the flap segment actuators into the outer mold line (OML) of the clean wing so that no external fairings or protuberances would adversely impact the drag characteristics of the wing. Detailed analytical models for the structural dynamic and aeroelastic behavior of the new model were created and validated by static loads and modal tests. Wind tunnel runs were carried out to measure lift / drag characteristics of the new model and to gain experience with its continuous communication with the data acquisition system of the wind tunnel and the commanding control algorithms created by SSCI and NASA.