The problem of efficient wind tunnel testing of multi-element airfoils is addressed. The design of an airfoil model with internal actuators positioning a flap in two degrees of freedom is reviewed. Preliminary low speed wind tunnel test results show that the approach is viable. Development of automated optimization procedures has started, as has a study of hysteretic effects observed when the flap stalls. Future development of end mount actuators and extension to 3-D testing is addressed.
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