Nakajima Hikari

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.

Variants

• Hikari 3 - 770 hp (574 kW)
• Hikari 1 - 820 hp (611 kW)

Applications

• Aichi D1A (D1A2)
• Aichi D3A (D3A1 first prototype)
• Mitsubishi F1M (F1M1 first prototype, second prototype initially)
• Nakajima A4N
• Nakajima B5N1 (B5N1 only)
• Nakajima C3N
• Yokosuka B4Y (B4Y1 fourth plane onward)

Specifications

General characteristics

• Type: 9-cylinder air-cooled radial aircraft piston engine
• Bore: 160 mm (6.30 in)
• Stroke: 180 mm (7.09 in)
• Displacement: 32.57 L (1,987.7 in³)

Components

• Cooling system: Air-cooled

Performance

• Power output: 611 kW (820 hp)

See also

Related development

• Nakajima Kotobuki

Nakajima Ha-8 (中島ハー８)

Related lists

• List of aircraft engines

References

• Classic Aeroplane Museum

Nihon Koukuuki Jiten