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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
Aichi D3A (prototype only)
Mitsubishi F1M
Nakajima A4N
Nakajima B5N1 (B5N1 only)
Nakajima C3N
Yokosuka B4Y

 

Specifications:
Type: 9-cylinder air-cooled radial aircraft piston engine
Bore: 160 mm (6.30 in)
Stroke: 180 mm (7.09 in)
Displacement: 32.57 lt (1,987.7 cu.in)
Cooling system: Air-cooled
Power output: 611 kW (820 hp)

 

 

 

 


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