Curtiss-Wright X-100

The Curtiss‑Wright X‑100 was an experimental tilt‑rotor aircraft developed in the United States during the early 1960s. Conceived by the Curtiss‑Wright Corporation as a proof‑of‑concept for combining the vertical‑takeoff capability of a helicopter with the speed and range of a fixed‑wing airplane, the X‑100 first flew on 19 April 1963. Its design featured two 14‑foot diameter, three‑bladed rotors mounted on short, pivoting pylons at the wingtips; the rotors could be tilted from a vertical orientation for hover to a horizontal position for conventional forward flight. The airframe was a lightweight aluminum semi‑monocoque structure, powered by a single Lycoming T53 turboshaft delivering 850 shaft horsepower. Flight tests demonstrated reliable transition between hover and cruise, achieving a top speed of 280 km/h (175 mph) and a service ceiling of 4,500 meters. Although the program was cancelled in 1965 due to budget constraints, the X‑100 provided invaluable data that directly influenced later successful tilt‑rotor programs such as the Bell XV‑15 and the modern V‑22 Osprey. Its legacy lies in proving that a mechanically simple, twin‑rotor tilt‑system could be integrated into a practical aircraft, shaping the future of vertical‑lift aviation.

Curtiss-Wright

Curtiss-Wright X-100

Classification

Design & Classification