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・ Caproni Ca.314
・ Caproni Ca.316
・ Caproni Ca.331
・ Caproni Ca.335
・ Caproni Ca.350
・ Caproni Ca.4
・ Caproni Ca.49
・ Caproni Ca.5
・ Caproni Ca.60
・ Caproni Ca.70
・ Caproni Ca.71
・ Caproni Ca.73
・ Caproni Ca.90
・ Caproni Ca.97
・ Caproni Campini Ca.183bis
Caproni Campini N.1
・ Caproni CH.1
・ Caproni PS.1
・ Caproni Sauro-1
・ Caproni Trento F-5
・ Caproni Vizzola 2
・ Caproni Vizzola Calif
・ Caproni Vizzola F.4
・ Caproni Vizzola F.5
・ Caproni Vizzola F.6
・ Caproni Vizzola Ventura
・ Caproni-Pensuti triplane
・ Capronia
・ Caproniella
・ Capronnieria


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Caproni Campini N.1 : ウィキペディア英語版
Caproni Campini N.1

The Caproni Campini N.1, also known as the C.C.2, was an experimental aircraft built by the Italian aircraft manufacturer Caproni. The N.1 was powered by a motorjet, a type of jet engine that powers the compressor using a conventional aircraft engine. The N.1 first flew in 1940, and as news of the Heinkel He 178's flight in 1939 had not yet been made public, the FAI listed the N.1 as the first successful jet-powered aircraft.〔Enzo Angelucci; Paolo Matricardi. ''Campini Caproni C.C.2 in Guida agli Aeroplani di tutto il Mondo''. Mondadori Editore. Milano, 1979, Vol. 5, pp. 218-9.〕 The N.1 was the only model in the series.
==Design and development==
In 1931, Italian engineer Secondo Campini submitted a report on the potential of jet propulsion to the ''Regia Aeronautica'', and demonstrated a jet-powered boat in Venice the following year. In 1934, the ''Regia Aeronautica'' granted approval for the development of a jet aircraft to demonstrate the principle.
As designed by Campini, the aircraft did not have a jet engine in the sense that we know them today. Rather, a conventional Isotta Fraschini L.121 RC.40 12-cylinder liquid-cooled piston engine was used to drive a three-stage variable-incidence compressor, which forced air into a combustion chamber where it was mixed with fuel and ignited. The exhaust produced by this combustion was to drive the aircraft forward. Campini called this configuration a "thermojet," but the term "motorjet" is in common usage today. It has also been described as a ducted fan.
The relatively small duct resulted in low mass flow, and thus low propulsive efficiency. In modern designs this is offset through high overall pressure ratios, but the N.1 had a low pressure ratio and thus low thermal efficiency as well. As a result, the engine had relatively low thrust, about 1,550 lbf, and very poor fuel economy.〔Marc de Piolenc and George Wright, ("Ducted Fan Design" ), Marc de Piolenc, 2001〕

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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