Nakajima Hikari
| 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
- 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
- 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
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
Related development
Related lists
References
- Goodwin, Mike & Starkings, Peter (2017). Japanese Aero-Engines 1910-1945. Sandomierz, Poland: MMPBooks. ISBN 978-83-65281-32-6.