Adaptive wing model for wind channel tests

Abstract

The aim of this work is to realize an adaptive wind channel wing model by means of a „structronic“ concept. The desired geometry changes are achieved through the use of the structural flexibility, and no moveable parts are required. The wind channel model presents two active sections: The „bump“ section, on the upper surface of the airfoil, and the adaptive trailing edge. The changes of the airfoil geometry by means of these parts of the model make possible to vary the distribution of the aerodynamic load on the wing. The activation of the bump and of the trailing edge is realized by means of solide state actuators. A sytem of ca. two hundred shape memory alloy actuators is used. The actuators give here also a contribution to the stiffness of the structure. Here the numerical results of the FEM investigations are presented, as well as the experimental results on the prototypes of the adaptive trailing edge and the bump actuators.