Pressure-distribution measurements on a tapered wing with a partial-span split flap in curved flight

Troller, TH (Daniel Guggenheim Airship Institute) Rokus, F (Daniel Guggenheim Airship Institute)
naca-tn-735
November 1939


Pressure-distribution tests were made on the 32-foot whirling arm of the Daniel Guggenheim Airship Institute of a tapered wing to determine the rolling and the yawing moments due to an angular velocity in yaw. The model was tested at 0 degree and 5 degree pitch; 0 degree, 5 degree, and 10 degree yaw; and with split flaps covering 25, 50, 75, and 100 percent of the wing span and deflected 60 degrees. The results are given in the form of load distributions and as calculated moment coefficients. The experimental values of rolling- and yawing- moment coefficients were in fairly close agreement with theory.

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