Nakajima Hikari
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This is the current revision of this page, as edited by 5.165.15.58 (talk) at 08:53, 5 October 2024 (Army designation edited - was Ha20, now Ha8. In the "Nakajima aircraft engines" list in the bottom of the page it marked as Ha8, also japanese version of the article calls the engine Ha8). The present address (URL) is a permanent link to this version.Revision as of 08:53, 5 October 2024 by 5.165.15.58 (talk) (Army designation edited - was Ha20, now Ha8. In the "Nakajima aircraft engines" list in the bottom of the page it marked as Ha8, also japanese version of the article calls the engine Ha8)
1930s Japanese piston aircraft engine
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| Hikari | |
|---|---|
| Type | Piston aircraft engine |
| Manufacturer | Nakajima Aircraft Company |
| Major applications | Aichi D1A |
| Developed from | Nakajima Kotobuki |
The Nakajima Hikari (Japanese: 光 "Light") was a nine-cylinder, air-cooled, radial aircraft engine developed in Japan for Navy use during World War II by the Nakajima Aircraft Company. It was a development of the Nakajima Kotobuki and Wright Cyclone. In Army use it was known as the Ha8.
Variants
[edit ]- Hikari 1
- 820 hp (610 kW)
- Hikari 1 kai
- 670–730 hp (500–540 kW)
- Hikari 2
- 750–840 hp (560–630 kW)
- Hikari 3
- 770 hp (570 kW)
Applications
[edit ]- Aichi D1A2
- Aichi D3A (first prototype)
- Kawasaki Ki-45 (first prototype)
- Mitsubishi F1M1
- Nakajima A4N
- Nakajima B5N1
- Nakajima C3N
- Yokosuka B4Y (B4Y1 fourth plane onward)
Specifications
[edit ]General characteristics
- Type: 9-cylinder air-cooled radial aircraft piston engine
- Bore: 160 mm (6.3 in)
- Stroke: 180 mm (7.1 in)
- Displacement: 32.57 L (1,988 cu in)
- Diameter: 1.375 mm
Components
- Cooling system: Air-cooled
Performance
- Power output: 820 hp (610 kW)
See also
[edit ]Related development
Related lists
References
[edit ]- Goodwin, Mike & Starkings, Peter (2017). Japanese Aero-Engines 1910-1945. Sandomierz, Poland: MMPBooks. ISBN 978-83-65281-32-6.