Tests of a tilting-rotor convertiplane, currently designated the XV-3, were made to investigate both mechanical and aerodynamic aspects of this type of aircraft. Only the longitudinal aerodynamic character istics are the subject of this report.nAircraft configuration variables were angle of attack, rotor-pylon angle, power, and longitudinal control. With the exceptions of a few runs at or near zero airspeed, and several propulsive efficiency runs at airspeeds up to 155 knots, most of the tests were made between approximately 60 and 120 knots. The tests at a given airspeed and pylon angle usually consisted in varying one of the aircraft variables with the others held constant. For each pylon angle setting, trim control and power settings simulating level flight of 4700 pounds gross weight were experimentally determined for at least one airspeed.
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