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Aviation History
1940
1940 - 2179.PDF
AUGUST I, 1940 91 lac oombs areTwo aspects 01 tne riat B.R.20 are seen in this Flight copyright drawing. fuselage floor. Just aft of the bomb bay is the lower gun position. ifc parallel portion of the that the machine is not entirely of stressed-skin type. The fuselage, for example, has a framework of welded chrome-molybdenum steel tube in the tail portion, which is covered with doped fabric. The front portion is a stressed-skin monocoque. In the structure of the wing also a mixed form of construction is em- ployed. There are two main spars, and the leading edge is metal covered while the trailing edge portion has a fabric covering over tubular ribs. The wing is built in three sections, the two outer tapering portions being attached to the centre section just outside the engine nacelles. Trailing-edge flaps are fitted. The retractable wheels of the under- carriage are raised backwards into the tail portion of the somewhat long engine nacelle fairings. The wheels are carried on high-tensile steel forks with oleo shock absorbers. Power Plant Power is supplied by two Fiat A.80 R.C.41 18-cyl. double-row radial engines. Two versions of the A.80 engine are available, the R.C.20 which develops 1,200 b.h.p. for take- off and 1,100 b.h.p. at 2,000 m. (4,400ft.), and the R.C.41, which gives 1,000 b.h.p. for take-off and develops 1,000 b.h.p. at 4,100 m. (13,500ft.). The standard version of the B.R.20 is fitted with the latter type. Hamilton Demoded : The original nose of theB.R.20 had a good deal of window framing obscuring the bomb-aimer'sview. Standard constant-speed airscrews built under licence by the Fiat com- pany are fitted. The following data relating to the Fiat A.80 R.C.41 engine may be of interest. The bore is 140 mm. and the stroke 165 mm., giving a capacity of 45.72 litres. The engine has a length of 1.62 metres and a diameter of 1.335 metres. The weight is 725 kg. (1,600 lb.). The power for take-off at 1,995 r.p.m. is 1,000 b.h.p., and at 2,200 r.p.m. it is 1,030 b.h.p. The normal engine speed at the operational altitude is 2,100 r.p.m. Reduction gearing gives a corresponding airscrew
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