Mitsubishi Kinsei
| Kinsei | |
|---|---|
| Type | Piston aircraft engine |
| National origin | Japan |
| Manufacturer | Mitsubishi Heavy Industries |
| First run | 1934 |
| Major applications | Aichi D3A Yokosuka D4Y3-D4Y4 Kawasaki Ki-100 |
| Number built | 12,228 |
| Developed from | Pratt & Whitney R-1690 Hornet |
| Developed into | Mitsubishi Zuisei, Mitsubishi Kasei, Ha-43(Ha-211) |
The Mitsubishi Kinsei (金星 Venus) was a 14-cylinder, air-cooled, twin-row radial aircraft engine developed by Mitsubishi Heavy Industries in Japan in 1934 for the Imperial Japanese Navy. The Mitsubishi model designation for this engine was A8 while it was an experimental project, in service it was known as the MK8 "Kinsei" by the Navy. In the middle of the war the engine was adopted by Army so it got designation Ha112[1] Unified designation code was Ha-33.
Cylinder and detail design was based on the single-row, 9-cylinder air-cooled Pratt and Whitney R-1689 Hornet, but underwent numerous modifications and improvements.[2]
Variants
- -3 - 910 hp
- -41 - 1,075 hp
- -42 - 1,075 hp
- -43 - 1,000 hp, 1,080 hp
- -44 - 1,000 hp, 1,075 hp
- -45 - 1,075 hp
- -46 - 1,070 hp
- -48 - 1,080 hp
- -51 - 1,300 hp
- -53 - 1,300 hp
- -54 - 1,200 hp, 1,300 hp
- -62 - 1,560 hp
Applications
- Aichi D3A
- Aichi E13A
- Aichi E16A
- Douglas L2D2-L2D5
- Kawanishi H6K
- Kawasaki Ki-96
- Kawasaki Ki-100
- Kawasaki Ki-102
- Nakajima/Mahshu Ki-116
- Mitsubishi A6M8
- Mitsubishi A7M
- Mitsubishi B5M
- Mitsubishi G3M
- Mitsubishi Ki-46
- Yokosuka D4Y3-D4Y4
Specifications (Kinsei-44)
Data from Jane's.[3]
General characteristics
- Type: 14-cylinder air-cooled twin-row radial engine
- Bore: 140 mm (5.5 in)
- Stroke: 150 mm (5.9 in)
- Displacement: 32.3 L (1,970 cu in)
- Length: 1,646 mm (64.8 in)
- Diameter: 1,218 mm (48.0 in)
- Dry weight: 545 kg (1,202 lb)
Components
- Valvetrain: Overhead valve, one inlet and one exhaust valve per cylinder, pushrod operated.
- Supercharger: Centrifugal, single speed.
- Oil system: Triple section pump, one pressure pump, two scavenge pumps.
- Cooling system: Air-cooled
- Reduction gear: Planetary gear, 0.7:1 ratio.
Performance
- Power output: 1,075 hp (802 kW) at 2,500 rpm at 2,000 m (6,560 ft) maximum.
- Specific power: 24.8 kW/L (0.56 hp/cu in)
- Compression ratio: 6.6:1
- Power-to-weight ratio: 1.5 kW/kg (0.9 hp/lb)
See also
- Related development
- Comparable engines
- BMW 801
- Bristol Hercules
- Fiat A.74
- Gnome-Rhône 14N
- Nakajima Sakae
- Pratt & Whitney R-1830
- Shvetsov ASh-82
- Wright R-2600
- Related lists
References
Notes
Bibliography
- Matsuoka Hisamitsu, Nakanishi Masayoshi. The History of Mitsubishi Aero Engines 1915-1945. Miki Press, Japan, 2005. ISBN 4-89522-461-9
- Gunston, Bill. World Encyclopaedia of Aero Engines. Cambridge, England. Patrick Stephens Limited, 1989. ISBN 1-85260-163-9
- Jane's Fighting Aircraft of World War II. London. Studio Editions Ltd, 1989. ISBN 0-517-67964-7
- Peattie, Mark R., Sunburst: The Rise of Japanese Naval Air Power 1909-1941, Annapolis, Maryland: Naval Institute Press, 2001, ISBN 1-55750-432-6
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