Kawasaki C-1

The Kawasaki C-1 (川崎 C-1) is a twin-engined short-range military transport aircraft, used by the Japan Air Self-Defense Force (JASDF). Development began in 1966 as the JASDF sought to replace its aging World War II–era Curtiss C-46 Commandos. Production commenced in 1971, and the aircraft remains in service. It will eventually be replaced by the Kawasaki C-2.

Variants
XC-1: Prototypes.
C-1/C-1A: Medium-range military transport version.
The last five C-1s ordered were fitted with an additional 4,730 litre fuel tank.
EC-1: electronic warfare training aircraft.
C-1FTB: Flight test bed used for testing various equipment.

Asuka/QSTOL: Quiet STOL research aircraft, developed by the National Aerospace Laboratory.
Powered by four FRJ710 turbofan engines and making use of the Coandă effect. It was built to research STOL using upper surface blowing, aircraft noise reduction, fly-by-wire systems and composite materials construction. The only example built is currently on display in Kakamigahara Aviation Museum in Gifu, Japan.
Note: Three C-1s were allocated to the MSDF as airborne minelayers under the Fourth Defense Buildup Plan (1972–76). It is unknown what designation was given to them, or indeed whether they were ever actually delivered.

Specifications (Kawasaki C-1)

General characteristics

• Crew: 2 flight crew and 3 mission crew
• Capacity: 8,000 kg (18,000 lb) normal payload
• Length: 29 m (95 ft 2 in)
• Wingspan: 30.6 m (100 ft 5 in)
• Height: 9.99 m (32 ft 9 in)
• Wing area: 120.5 m² (1,297 sq ft)
• Aspect ratio: 7.8
• Empty weight: 23,220 kg (51,191 lb)
• Max takeoff weight: 38,700 kg (85,319 lb)
• Fuel capacity: 15,200 l (4,000 US gal; 3,300 imp gal) in 4 integral tanks in the wings
• Powerplant: 2 × Pratt & Whitney JT8D-M-9 (Mitsubishi built) low bypass turbofans>, 64 kN (14,500 lbf) thrust each

Performance

• Maximum speed: 806 km/h (501 mph; 435 kn) at 7,620 m (25,000 ft) at 35,450 kg (78,150 lb)
• Cruise speed: 657 km/h (408 mph; 355 kn) at 10,670 m (35,010 ft) at 35,450 kg (78,150 lb)
• Range: 3,353 km (2,083 mi; 1,810 nmi) with max fuel & 2,300 kg (5,100 lb) payload
• Service ceiling: 11,580 m (37,990 ft)
• Rate of climb: 17.75 m/s (3,494 ft/min) at sea level
• Wing loading: 321.2 kg/m² (65.8 lb/sq ft)
• Thrust/weight: 0.003 kN/kg (0.34 lbf/lb)