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DC-4 Skymaster

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).

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Specifications
aa.VehicleDOUGLAS DC-4-1009 SKYMASTER
ab.WeightEmpty 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.Length93ft 11 in ( 28.79m)
ad.WidthWingspan: 117ft 6 in (35.82)
ae.Height27ft 7 in (8.41m)
af.Crew4 Crew + 54-66 passengers/troops
ag.ArmourNone
ah.Primary ArmamentNone
ai.Secondary Armamentnone
aj.Engine4 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/Weight0.0787 hp/lb (0.1294 kW/kg) at maximum gross weight with take-off power
as.Operating Range3,300 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-OffroadMaximum 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 Capacity2,868 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 
azGradient 
ba.Side Slope 
bb.Vertical Step 
bc.Trench 
bd.Fording 
ca.Propellers3-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 Area1,460 sq ft (136 m2)
cf.Aspect Ratio 
cg.Airfoilroot: NACA 23016; tip: NACA 23012
ch.Wing Loading50.1 lb/sq ft (245 kg/m2) at maximum gross weight
ci.Take-off Run 
cj.Landing Run 
ck.Time to Altitude: 
None
 
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