11/30/2013. Remarks by Johan Visschedijk: "In 1978 the Technical Research and Development Institute of the Japan Defense Agency chose the Mitsubishi T-2 supersonic trainer as the basis for a control-configured vehicle intended to provide experience with and engineering data for active flight-control technologies. These were designed to provide much improved general agility, together with the ability to point the nose considerably off the line of flight, thereby opening distinct combat advantages.

Mitsubishi began work on the aeroplane in April of the same year, and the aircraft finally emerged as an inherently unstable type with a triplex digital fly-by-wire control system tied into the standard control surfaces (modified with carbon fiber "flaperons" and leading edge flaps) as well as two movable canard surfaces on the inlet trunks forward of the wings and, in line with these surfaces but under the fuselage, a vertical fin.

Powered by two 7,066 lb (3,205 kg) st Ishikawajima-Harima TF40-IHI-801A (license-built Rolls-Royce Turboméca Adour Mk.801A) turbofans, the T-2CCV first flew in August 1983, and a successful test program yielded valuable results in control augmentation, relaxed static stability, maneuver load control, direct lift control, and direct side-force control."

Span: 25 ft 10.25 in (7.88 m)
Length: 58 ft 6.25 in (17.84 m)
Height: 14 ft 4.25 in (4.38 m)
Wing area: 252.49 sq.ft (23.46 sq.m)
Max take off weight: 21,616 lb (9,805 kg)
Max speed: 748 mph (1,204 kmh) at 36,000 ft (10,975 m)
Service ceiling: 50,000 ft (15,240 m)
Range: 1,612 mls (2,594 km)