Pratt & Whitney R-985
From Wikipedia, the free encyclopedia
| R-985 Wasp Junior | |
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| Pratt & Whitney R-985 AN-1 | |
| Type | Radial engine |
| National origin | United States |
| Manufacturer | Pratt & Whitney |
| First run | 1929 |
| Number built | 39,037 |
| Developed from | Pratt & Whitney R-1340 |
The Pratt & Whitney R-985 Wasp Junior was a radial engine widely used in American aircraft starting in the 1930s.[1] It was a scaled-down version of the original R-1340, and the second in the Wasp family. It was a single-row, 9-cylinder air-cooled radial design. Displacement was 987 in³ (16.2 L); bore and stroke were each 53⁄16 in (132 mm).
It was used on numerous light aircraft and has a good reputation for being dependable. Most versions produced 450 hp (336 kW). A total of 39,037 engines were built.[2]
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[edit] Applications
- Airspeed Oxford
- Air Tractor AT-300
- Avro Anson
- Barkley-Grow T8P-1
- Beechcraft Staggerwing D-17S, D-17W, G-17S
- Beech Model 18
- Bellanca CH-300
- Berliner-Joyce OJ-2
- Bratukhin G-3
- BT-13 Valiant
- CAC Winjeel
- De Havilland Canada DHC-2 Beaver
- Grumman Ag Cat
- Grumman Goose
- Howard DGA-11
- Howard DGA-15
- Lockheed L-10 Electra
- Lockheed Model 12 Electra Junior
- PWS-24
- Sikorsky R-5
- Spartan Executive
- Vought Kingfisher
[edit] Specifications (R-985-TB)
Data from [3]
General characteristics
- Type: Nine-cylinder single-row supercharged air-cooled radial engine
- Bore: 5.2 in (132 mm)
- Stroke: 5.2 in (132 mm)
- Displacement: 985 in³ (16.14 l)
- Length: 41.61 in (1,057 mm)
- Diameter: 45.75 in (1,162 mm)
- Dry weight: 611 lb (277 kg)
Components
- Valvetrain: Two overhead valves per cylinder
- Supercharger: Single-speed General Electric centrifugal type supercharger, 8:1 reduction
- Fuel system: Two-barrel Stromberg carburetor
- Fuel type: 80 octane rating gasoline
- Cooling system: Air-cooled
Performance
- Power output: 440 hp (328 kW) at 2,300 rpm for takeoff
- Specific power: 0.45 hp/in³ (20.32 kW/l)
- Compression ratio: 6.0:1
- Specific fuel consumption: 0.49 lb/(hp•h) (295 g/(kW•h))
- Oil consumption: 0.39 oz/(hp•h) (15 g/(kW•h))
- Power-to-weight ratio: 0.72 hp/lb (1.18 kW/kg)
[edit] See also
Related development
Related lists
[edit] References
[edit] Notes
- ^ Gunston 1989. p.115.
- ^ Pratt & Whitney - R-595 page Retrieved: 25 October 2008
- ^ Tsygulev (1939). Aviacionnye motory voennykh vozdushnykh sil inostrannykh gosudarstv (Russian: Авиационные моторы военных воздушных сил иностранных государств). Moscow: Gosudarstvennoe voennoe izdatelstvo Narkomata Oborony Soyuza SSR. http://base13.glasnet.ru/text/aviamotory/t.htm.
[edit] Bibliography
- Gunston, Bill. World Encyclopedia of Aero Engines. Cambridge, England. Patrick Stephens Limited, 1989. ISBN 1-85260-163-9
[edit] External links
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