A 1/6-scale, semispan model of an AFTI-111 concept equipped with eleven remotely controllable hydraulic actuation systems used to control wing shape and horizontal tail angle was tested in the Propulsion Wind Tunnel (16T) at free-stream Mach numbers of 0.60 and 0.85 and free-stream dynamic pressures of 400 and 500 psf. Angle of attack was varied from 0 to 8 deg. The objectives of this test were to further develop and refine a computer-controlled self-optimizing wing for continual investigation of optimum wing airfoil contours for specific mission profiles. (Author)


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