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DESIGN AND WIND TUNNEL TEST OF A MODEL HELICOPTER ROTOR HAVING AN INDEPENDENTLY MOVABLE INBOARD BLADE PANEL
BOEING CO MORTON PA VERTOL DIV
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Wind tunnel tests of a rotor having an independently movable inboard blade panel were conducted at an advance ratio of 0.6. It was demonstrated that this design resulted in a major advance in propulsive capability over the conventional type of rotor. Test results are presented in nondimensional plots of lift, power, and propulsive force versus control axis angle, and in cross- plotted contours of constant power of lift versus propulsive force axes.
APPROVED FOR PUBLIC RELEASE