The report presents the results of wind tunnel test BVWT 055 performed in the Boeing Vertol V/STOL wind tunnel on a powered four prop tilt wing semi-span model. The purpose of the test was to establish the effect of leading edge boundary layer control (BLC) coupled with cyclic pitch on the descent capability of the aircraft. Configuration changes including 'both-down- between-nacelles' and 'both-down-inboard' propeller rotations, double slotted flaps and single slotted flaps, full span leading edge slats on and off, and all but the inboard wing fence removed were investigated during this test.
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