The design featured a belt clutch and a transmission which could be engaged to spin the rotor blades to high speed before take-off to produce short takeoff runs. A lever on the rear cockpit wall would select the drive position for the transmission. A single "spin-up lever" on the cockpit left side would then be pressed downward, operating as a collective pitch control to put the blades into flat pitch while simultaneously tensioning the belt clutch. The rotor could be spun to over 500 rpm before takeoff, well above the normal flight range (typically 425 rpm). Release of the spin-up lever would disengage both the clutch and the transmission, while placing the blades into flight pitch. After a very brief takeoff run (typically 25 to 200 feet, depending upon load and winds) adequate flight airspeed would be attained, while the rotor speed decayed to the normal flight range. The rotor was not engine-driven in flight. A strong spring resisted accidental depressing of the spin-up lever while airborne. Dual controls were provided for all functions except the spin-up lever, which was accessible only from the left seat. The aircraft enjoyed nimble handling with light control forces, but suffered from a shallow climb gradient. The rotor system (hub and blades) is very similar to that found on the early versions of the Hughes 269 / Schweizer 300 series helicopters. The primary difference is in the twist of the blades (or lack thereof), optimized for autorotation in the case of the J-2. In 1974, the rights were bought by Aero Resources, who planned to return the Super J-2 to production, but could not find a market for the aircraft and no more were built.
