Douglas DC-8 (piston airliner)
Proposed airliner project From Wikipedia, the free encyclopedia
The Douglas DC-8 was an American piston-engined airliner project by Douglas Aircraft. A concept developed more than a decade before the DC-8 jetliner, the piston-engined DC-8 was to have propellers in the tail, an idea first used at Douglas by Edward F. Burton on a fighter project.[1] The airliner project was canceled after development costs made it commercially unviable.
| DC-8 | |
|---|---|
| Role | Airliner |
| Manufacturer | Douglas Aircraft |
| Status | Project canceled |
| Developed from | Douglas XB-42 Mixmaster |
Design and development
Summarize
Perspective
Based on the cancelled XB-42,[2] the program began shortly after the end of World War II. It was intended to operate on short- and medium-range routes, carrying between 40 and 48 passengers[2] in a then-novel pressurized cabin[2] (which had been pioneered by the Boeing 307 in 1938, but was still not in standard airline use).
The DC-8 was to use the same Allison V1710s as the XB-42[3] (these rated at 1,375 hp (1,025 kW)),[2] fitted below and immediately behind the cockpit.[2] They were to power contra-rotating propellers in the tail,[4] as in the XB-42, by way of driveshafts under the cabin floor[2] (an arrangement reminiscent of the P-39). This arrangement, also proposed for the Douglas Cloudster II general aviation aircraft, reduced drag by 30% and eliminated the problems associated with controlling the aircraft with one engine out.[5][6] Cabin access would have been by airport stair through a single portside door.[7]
Despite performance predicted to significantly surpass conventional twin airliners,[2] excessive complexity and high development costs[2] (with consequent high sales price and operating costs)[2] meant that less risky types, such as Convair's 240 and Martin's 2-0-2, were preferred,[3] and the DC-8 was dropped before a prototype was built.
Specifications (estimated)
Data from DC-8 that might have been [8]
General characteristics
- Crew: three
- Capacity: 40-48 passengers
- Length: 77 ft 8 in (23.67 m)
- Wingspan: 110 ft 2 in (33.58 m)
- Height: 26 ft 9+3⁄4 in (8.17 m)
- Wing area: 1,104 sq ft (102.6 m2)
- Aspect ratio: 11:1
- Airfoil: Douglas S-17
- Empty weight: 24,415 lb (11,074 kg)
- Gross weight: 40,000 lb (18,144 kg)
- Powerplant: 2 × Allison V-1710-G4L/R liquid-cooled V12 engine, 1,600 hp (1,200 kW) each (take-off power)
Performance
- Maximum speed: 280 mph (450 km/h, 240 kn) at 20,200 ft (6,200 m))
- Cruise speed: 237 mph (381 km/h, 206 kn) at 10,000 ft (3,050 m) - 60% power
- Range: 2,370 mi (3,810 km, 2,060 nmi)
- Service ceiling: 30,500 ft (9,300 m)
- Rate of climb: 940 ft/min (4.8 m/s)
See also
Related development
Bibliography
External links
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