Design and Construction of a Wind Tunnel Model with Active Variable Camber Continuous Trailing Edge Flap for Aeroelastic “In-Flight” Shape Optimization Tests

Abstract

An aeroelastically scaled wing wind tunnel model was designed and fabricated 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 that can be actively driven while testing is underway. Development of the model follows the successful development and wind tunnel tests of smaller VCCTEF configured aeroelastic models which were fitted with manually adjusted flaps. The new active model packages the flap actuators completely within the outer mold line of the wing. Detailed analytical models for the structural dynamic and aeroelastic behavior of the new model were validated by static loads and modal tests. Wind tunnel runs were carried out to measure lift and 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 control algorithms. The wind tunnel model is available for further testing.