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|  | Douglas DC-4 1009 Skymaster: The DC-4 was planned in 1936 as a long-range civil air transport with four engines, retractable tricycle landing gear and greater carrying capacity than the very successful DC-3 commercial airliner. A pressurised DC-4 (later called the DC-4E) prototype first flew in June 1938, but technical problems with the aircraft forced Douglas to drop the project. Instead, an unpressurised and simplified DC-4 with a lighter structure, new high aspect ratio wing and a tail unit with a single central vertical surface was selected for production. Powered by Pratt & Whitney R-2000-2SD1-G Twin Wasp radial engines it went straight into production for military purposes - as a result of World War II - with the first example having yet to fly. The DC-4 entered military service with the US Army in February 1942 as the Douglas C-54 Skymaster (Army) and R5D (Navy) long-range military transport. The main military versions were the impressed C-54's (26 passengers), fully militarised C-54A's and R5D-1's (50 passengers), the C-54B's and R5D-2's with integral wing tanks, the C-54D's and R5D-3's, the C-54E and R5D-4 convertible freight/passenger models with revised fuel tankage, and the C-54G and R5D-5 troop carriers. One of the two civil models produced after WWII was the DC4-1009, capable of carrying 54-66 passengers and cabin crew (excluding pilot and co-pilot). Post your comments and feedback on the DC-4 Skymaster here... |
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| aa. | Vehicle | DOUGLAS DC-4-1009 SKYMASTER |
| ab. | Weight | Empty weight: 43,300 lb (19,641 kg); Gross weight: 63,500 lb (28,803 kg); Max takeoff weight: 73,000 lb (33,112 kg) |
| ac. | Length | 93ft 11 in ( 28.79m) |
| ad. | Width | Wingspan: 117ft 6 in (35.82) |
| ae. | Height | 27ft 7 in (8.41m) |
| af. | Crew | 4 Crew + 54-66 passengers/troops |
| ag. | Armour | None |
| ah. | Primary Armament | None |
| ai. | Secondary Armament | none |
| aj. | Engine | 4 x Pratt & Whitney R-2000-2SD13-G Twin Wasp 14-cylinder air-cooled radial piston engines, 1,450 hp (1,080 kW) each for take-off 1,100 hp (820 kW) at 14,000 ft (4,300 m) |
| ak. | Power/Weight | 0.0787 hp/lb (0.1294 kW/kg) at maximum gross weight with take-off power |
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| as. | Operating Range | 3,300 mi (5,300 km, 2,900 nmi) at 10% above max L/D speed; Ferry range: 4,250 mi (6,840 km, 3,690 nmi) with inner wing fuel cells |
| at. | Speed-Offroad | Maximum speed: 280 mph (450 km/h, 240 kn) at 14,000 ft (4,300 m); Cruise speed: 227 mph (365 km/h, 197 kn) 60% power at 10,000 ft (3,000 m) Maximum cruise speed 246 mph (214 kn; 396 km/h) at 20,000 ft |
| au. | Speed-Road | |
| av. | Fuel Capacity | 2,868 US gal (2,388 imp gal; 10,860 l) normal capacity or 3,592 US gal (2,991 imp gal; 13,600 l) with alternative inner wing tanks |
| aw. | Fuel Consumption | |
| ax. | Fuel Type | |
| ay. | Clearance | |
| az | Gradient | |
| ba. | Side Slope | |
| bb. | Vertical Step | |
| bc. | Trench | |
| bd. | Fording | |
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| ca. | Propellers | 3-bladed Hamilton-Standard Hydromatic, 13 ft 1 in (3.99 m) diameter constant-speed propellers |
| cb. | Endurance | |
| cc. | Service Ceiling | |
| cd. | Rate Of Climb | |
| ce. | Wing Area | 1,460 sq ft (136 m2) |
| cf. | Aspect Ratio | |
| cg. | Airfoil | root: NACA 23016; tip: NACA 23012 |
| ch. | Wing Loading | 50.1 lb/sq ft (245 kg/m2) at maximum gross weight |
| ci. | Take-off Run | |
| cj. | Landing Run | |
| ck. | Time to Altitude: | |
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