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Aviation History
1939
1939 - 0415.PDF
FEBRUARY 16, 1939 FLIGHT. 155 In this drawing the general arrangement in the long-range twelve-seater version is shown. It will be seen that freight and a certain proportion of luggage is carried under the raised floor of the pilot's compartment. Various items of equipment, including the rear of the instrument panel, can be reached through the hinged nose. teen-seventeen seater 19ft. (5.8 m.) ; and for the twenty-seater 21ft. 8in. (6.6 m.). In addition to the normal windows there are four which may be used as emergency exits, while there are two exits in the roof, one in the passenger's compartment and one in the control cabin. The windows are of the double- pane type, which provide insulation against sound and cold. The air in the cabin is steam-heated and the temperature is controlled, while each passenger has, as usual, an individual supply of dry cold air. Structurally, -the most interesting feature of the Flamingo is the wing, which is made up in four sections, consisting of a pair of stub wings and a pair of outer wings. The former carry the engine and undercarriage assemblies, the fuel tanks, and the inner section of the flaps. The centre section has one main spar (a lattice girder of extruded aluminium alloy) and the two auxiliary spars, which are Wagner beams with alloy extruded flanges. The under carriages and the engine mountings are carried on rigid bulk head ribs lying transversely between the spars. The four fuel tanks, two on each side of the main spar, are carried outboard DE HAVILLAND D.H.95 Two Bristol Perseus XIIc Engines Span ... Length overall (tail up) ... Width (extension planes and airscrews removed) Packing width of fuselage (wings and stubs removed) ... : Height overall (tail down) Wing area (including fuselage centre section) Power loading (17,000 lb. or 7,710 kg.) at take-off, power (1,780 b.h.p.) Span loading Wing loading Flap chord Flap area Tailplane area (gross) Elevator area (total) Fin area (total) Rudders area (total) Aileron area (total) Undercarriage track Weights. Tare weight (12-seater to standard specification, including 200 lb., 90 kg. allowance for radio, but excluding automatic pilot, parachute flares, de-icing equipment) Crew of three Fuel 314 gals. (1,428 litres), at 7.5 lb/ gal. (0.75 kgjl.) Fuel 195 gals. (1,428 litres) at 7.5 lb./gal. J0.75 *«//.) .' ... *... Oil 22 gals. (100 litres) at 9.0 lb./gal. (0.9 *g/*o rayload available for passengers, lug gage, mail and freight >adings. 68ft. (20.70 m.) 50ft. 7in. (15.45 m.) 25ft. 4in. (7.73 m.) 9ft. (approx.) 15ft. 3in. (4.65 m.) 639 sq. ft. (59.3 sq. m.) 9.55 lb./b.h.p. (4.27 kg/c.v.) En gine Boost cm. of Ib./sq in. mercurv. Max. cruising ... ... 1.25 Max. climbing (inter national rating) ... 1.25 Max. take-off 3 Max. economical cruis ing —1 Max. for level flight (Sniin.) 1.25 6.5 6.5 15.6 -5.2 6.5 Power. Engine R.P.M. 2,250 2,250 2,700 2,200 2,600 B.H.P. 655/685 680/710 865/890 530 815 Altitude. ft. S.L. 4,000 S.L. 9,000 6,000 m. S.L. 1,220 S.L. 2,750 1,830 3.68 Ib./sq. ft. (18.0 kglsq. m.) 26.6 lb./sq, ft. (13.0 kglsq. m.) 20 per cent, of wing. 71 sq. ft (6.60 sq. m.) 73.8 sq. ft. (6.86 sq. m.) 50.6 sq. ft. (4.70 J?- »•) 38 sq. ft. (3.53 sq. m.) 36.7 sq. ft. (3.41 sq. m.) 46.0 sq. ft. (4.27 sq. m.) 20ft. 8in. (6.30 m.) Performance Loaded to 17,000 lb. (7,710 kg.) Total all-up weight With 1,000 miles (1,610 km.) range in still air. lb. kg. 11,325 510 2,354 — 198 2,613 17,000 5,142 230 1,066 — 90 1,182 7,710 With 500 miles (805 km.) range in 40 m.p.h. headwind (64.5 km/hr.) lb. kg. 11,325 510 — 1,462 198 3,505 17,000 5,142 230 — 663 90 1,585 7,710 Maximum economical cruising speed at 10,000ft. (3,050 m.) with 500 b.b.p. per engine ... ... - Maximum economical cruising speed at sea- level with 485 b.h.p. per engine. Maximum continuous cruising speed at 5,000ft. (1,525 m.) Maximum all-out level speed at 7,500ft. (2,290 m.) Take-off run in 5 m.p.h. (8 kmlkr.) wind (on 17,000 lb.) Height at 650 yd. (600 m.) from rest in 5 m.p.h. (8 kmlkr.) wind ... Landing run in 5 m.p.h. (8 km/hr.) wind... Rate of climb at sea-level on take-off power Rate of climb at sea-level on climb power... Time to climb to 5,000ft. (1,525 m.) Time to climb to 10,000ft. (3,050 m.) Time to climb to 15,000ft. (4,575 m.) Absolute ceiling Service ceiling Fuel consumption at maximum economical cruising speed at lQ.OOOft. (3,050 m.) ... Air miles per gallon -, Ultimate range with full fuel, 410 gals. (1,860 litres) Absolute ceiling with one engine stopped... Rate of climb with one engine stopped ... Rate of climb at sea-level with one engine stopped and other at take-off power ... 204 m.p.h. (328 kmlkr.) 184 m.p.h. (296 kmlkr.) 227 m.p.h. (365 kmlkr.) 243 m.p.h. (391 kmlkr.) 250 yd. (228.5 m.) 170 ft. (52 m.) 275 yd. (251.5 m.) 1,500 ft./min. (457.5 (m,'min.) 1,050 ft./min. (320.5 mjmin.) 4.7 min. 10.6 min. 21.0 min. 20,150ft. (6,150.0 m.) 18,500ft. (5,650.0 ».) 64 gals./hr. (291 litrtslhr.) 3.18 m.p.g. (1,125 kmlliire) 1,305 miles (2,100 km.) 8,000ft. (2,440 m.) 150 ft./min. (45.7 m/min.) 250 ft./min. (76.2 mfmrn.)
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