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Armstrong Siddeley Deerhound : ウィキペディア英語版
Armstrong Siddeley Deerhound

The Armstrong Siddeley Deerhound was a large aero engine developed by Armstrong Siddeley between 1935 and 1941. An increased capacity variant known as the Boarhound was never flown,〔Gunston 1989, p.18.〕 and a related, much larger, design known as the Wolfhound existed on paper only. Development of these engines was interrupted in April 1941 when the company's factory was bombed, and on 3 October 1941 the project was cancelled by the Air Ministry.
==Design and development==
The Deerhound I was a triple-row, 21-cylinder, air-cooled radial engine design with the unusual feature of inline cylinder banks. Unlike earlier Armstrong Siddeley engines the Deerhound used overhead camshafts to operate its poppet valves, using one camshaft for each bank of three cylinders.〔Lumsden 2003, p.77.〕
Flight testing began in 1938 using an Armstrong Whitworth Whitley II, serial number ''K7243'', during which cooling problems were encountered with the rear row of cylinders. This problem was solved by a 'reversed-flow' cooling system, in which a large air duct at the rear of the cowling took in air and directed it forward to exit behind the propeller.〔Lumsden 2003, p.77.〕 The project suffered a severe setback when the Whitley crashed on takeoff in March 1940, fatally injuring its crew. The accident was attributed to an incorrect elevator trim setting and was not related to the engines.〔Lumsden 2003, p.77.〕 A single prototype Deerhound III was built and ran, and survived until the late-1970s before being scrapped. Development work on the early engines was cancelled by the Air Ministry on 23 April 1941, but running of the Mk III was allowed to continue until 3 October 1941; at this point all records were ordered to be handed over to Rolls-Royce.

A projected increased capacity variant known as the Boarhound was planned but never built, and a related much larger design, the Wolfhound, existed on paper only. The latter engine featured six banks of four cylinders, a displacement of around 61 litres (3,733 cu in) and a projected takeoff power rating of .

抄文引用元・出典: フリー百科事典『 ウィキペディア(Wikipedia)
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