The Rockwell XFV-12 was an experimental supersonic fighter prototype developed for the United States Navy in the 1970s. It was designed to have vertical takeoff and landing (VTOL) capability and a speed of Mach 2.
Design and Technology
This aircraft had a unique design to support operations from small aircraft carriers called Sea Control Ships.
Thrust Augmented Wing (TAW): Utilized a thrust-augmenting wing concept, where holes in the wing, similar to "Venetian blinds," would open to direct engine jets downward to generate vertical lift.
Wing Configuration: With a rear main wing and canards (winglets) at the front, measuring nearly 50% of the main wing area.
Combined Parts: To reduce costs, this prototype used the nose section from a Douglas A-4 Skyhawk and intakes from a McDonnell Douglas F-4 Phantom II.
Technical Specifications (Design Targets)
According to data from Wikipedia and Aviastar.org, the aircraft's performance targets included:
Maximum Speed: Mach 2.2 to 2.4 (approximately 2,560 km/h).
Engine: One Pratt & Whitney F401-PW-400 afterburning turbofan.
Armament: Planned to carry one M61A1 Vulcan 20mm internal cannon, two AIM-7 Sparrow missiles, and wingtip rails for AIM-9 Sidewinder missiles.
Dimensions: Approximately 13.39 meters long with a wingspan of 8.69 meters.
Failure and Cancellation
Although the technology was considered innovative, the program was ultimately terminated in 1981 for the following reasons:
Lack of Lift: Tests showed that the wing system could only generate 70-75% of the aircraft's total weight, making it impossible to achieve a vertical takeoff without the aid of a towline (untethered).
Technical Issues: Complex air ducting caused a significant reduction in thrust compared to initial estimates.
Strategy Change: The US Navy ultimately preferred conventional fighters like the F/A-18 Hornet and adopted the more proven AV-8B Harrier II VTOL aircraft.
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