Doman LZ-4
| LZ-4 | |
|---|---|
| Role | Experimental helicopter |
| National origin | United States |
| Manufacturer | Doman Helicopters Inc. |
| Designer | Glidden S. Doman |
| First flight | November 1950 |
| Number built | 1 |
| Developed from | Doman LZ-2A Pelican |
The Doman LZ-4 was an American eight-seat helicopter designed and developed by Doman Helicopters of Danbury, Connecticut.[1][2]
Design and development[edit]
Following the test flying of the Doman LZ-2A, Doman Helicopters developed an eight-seat helicopter with the designation LZ-4.[1] The fuselage had 3 rows of double seats in the main cabin and a two-crew flight deck in the front. Large folding doors allowed for loading bulky cargo into the main compartment. The tail boom was conventional with a cranked-up rear section mounting a tail rotor, and the helicopter was supported by a four-leg undercarriage.[3]
Specifications (LZ-4)[edit]
Data from Aerofiles : Doman LZ-4,[1] vertipedia Doman LZ-4[4]
General characteristics
- Capacity: 8
- Length: 38 ft 1 in (11.61 m)
- Height: 11 ft 2 in (3.41 m)
- Empty weight: 2,970 lb (1,347 kg)
- Gross weight: 4,773 lb (2,165 kg)
- Max takeoff weight: 4,700 lb (2,132 kg)
- Powerplant: 1 × Lycoming SO-580-B 8-cyl air-cooled horizontally-opposed piston engine, 400 hp (300 kW) for take-off
- Main rotor diameter: 48 ft 0 in (14.64 m)
- Main rotor area: 1,809.5 sq ft (168.11 m2)
Performance
- Cruise speed: 78 mph (125 km/h, 67 kn)
- Range: 209 mi (336 km, 181 nmi)
- Service ceiling: 16,001 ft (4,877 m)
- Rate of climb: 790 ft/min (4 m/s)
- Disk loading: 2.60 lb/sq ft (12.68 kg/m2)
References[edit]
- ^ a b c "American airplanes: Da - Dy". www.aerofiles.com. 11 March 2009. Retrieved 19 November 2011.
- ^ The Illustrated Encyclopedia of Aircraft (Part Work 1982-1985). Orbis Publishing. p. 1455.
- ^ R.Simpson "Airlife's Helicopter and Rotorcraft", 1998
- ^ "Vertipedia - Doman LZ-4 (CW-40)". vertipedia.vtol.org. Retrieved 28 January 2019.