|Artist's concept of the C-132|
|National origin||United States|
|Manufacturer||Douglas Aircraft Company|
|Developed from||C-124 Globemaster II|
The Douglas C-132 was a proposed transport aircraft, based on the company's C-124 Globemaster II. Design studies began in 1951 but the project was cancelled in 1957 by the USAF. No prototype was built and the project did not get past the mock-up stage. The C-132 was to be powered by four 15,000 shp (11,000 kW) Pratt & Whitney XT57 (PT5) turboprops, mounted on a swept wing. An air refueling version, the XKC-132 was also proposed, but it would only have utilized the probe and drogue (P&D) air refueling system and that system, used primarily by the US Navy, did not find favor with the USAF. One XT57 was installed in the nose of a C-124 (AF serial number 52-1069) for testing. Projected speed was to be 418 knots (774 km/h) with a range of 2,200 nautical miles (4,100 km) and a maximum payload of 137,000 pounds.
- Crew: 5
- Length: 183 ft 10 in (56.03 m)
- Wingspan: 186 ft 8 in (56.90 m)
- Wing area: 4,201 sq ft (390.3 m2)
- Max takeoff weight: 389,500 lb (176,674 kg) cargo configuration
- 469,225 lb (212,837 kg) tanker configuration
- Powerplant: 4 × Pratt & Whitney T57-P-1 turboprop engines, 15,000 shp (11,000 kW) each
- Propellers: 4-bladed constant-speed fully-feathering reversible propellers, 20 ft (6.1 m) diameter
- Range: 2,530 mi (2,199 nmi; 4,072 km) carrying 137,000 lb (62,000 kg) of cargo
- 5,180 mi (4,500 nmi; 8,340 km) carrying 74,700 lb (33,900 kg) of cargo
- Combat range: 2,475 mi (2,151 nmi; 3,983 km) transferring 19,550 US gal (16,280 imp gal; 74,000 l) of fuel
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- Connors, p.294
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- AAHS Journal Vol.50, No.1, pp. 13–27, Douglas C-132
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