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Aviation History
1936
1936 - 0174.PDF
8o FLIGHT. JANUARY 23, 193.5. The lower wing roots of the D.H.90 are of thick section, and in addition to carrying the wing bracing as cantilever beams they contain the two main petrol tanks, each of 30 gallons capacity, and also carry the engine mountings and undercarriage structure. or plywood can be bent in one direction but not in two. In other words, it can be bent around a cylinder, but not around a sphere or barrel. In the D.H.90 the sides of the cabin portion of the fuselage, back to the luggage compartment, are bent to a double curvature. They are curved as seen from in front, and they are slightly curved in plan view. By experimenting, the De Havilland engineers found that if dies were used and the plywood pressed before the cement had set, it was possible to persuade the sheet to adapt itself to the double curvature. The process has now been undertaken by Saunders-Roe as a commer cial proposition, and the cement used is a syn thetic resin -applied under heat and pressure. Aft of the luggage compartment the sides are curved in one direction only, i.e., they are. straight in plan view. Consequently ordinary flat sheets can be used for the covering. Although the top and bottom of the fuselage of the D.H.90 are flat, the "corners" have a pronounced radius. These are built up of strip:? of plywood tapered off and fitted together so as to produce the desired curve, and are then glued together in the curved state. Extreme stiffness is obtained in this way, and even a considerable local pressure fails to dent these curved pieces. The only equivalents of normal longerons are light longitudinal members which serve merely to pro vide a surface on which the fuselage sides and curved corners can be glued. Regarded from the user's point of view, the De Havil land Dragonfly is a five-seater with roomy cabin accommo dation and an exceptionally complete equipment supplied as standard. No attempt has been made to provide a Dimensions Length o.a Wing span (upper) Wing span (lower) Height o.a Engine centres Areas. Wings Effective bodv arm ... Total Fin Rudder Ailerons Tail plane Elevators Weights. Tare (incl. standard removable equipment) Pilot Passengers (4).. . . Fuel (normal, 60 gals. •--• 273 i) Oil (7 gals. - 32 .') Luggage With full tanks (85 gals. = 387 1) the pay load is reduced by 193 lb. (88 kg). ft. in. 31 8 43 0 38 6 9 2 10 8 10 8 S(|. ft. 256 32 288 7.8 11.0 17.0 17.1 14.5 lb. 2,490 170 640 462 68 170 D H.90 Two 130 m 11,78 13,11 11,73 2.7!) 3,23 3,2a 23,77 2,97 26,74 0,68 1.02 1,63 1.5U 1,33 kS 1131 77 200 210 31 77 " DRAGONFLY." h.p. Gipsy Major. Performance Max. speed, sea level... Cruising speed (1,000 ft.) at 2,100 r.p.m. ... Cruising speed (1,000 ft.) at 2,050 r.pjn. ... Cruising consumption (2,050 r.p.m.) Ultimate range (60 gals.) Ultimate range (85 gals.) Take-off run-in 5 m.p.h. (8 kmjh) wind Height at 656 yds. (600 m) from rest Distance to stand-still from 50 ft. (13,3 m)... Gliding angle, flaps up Gliding angle, flaps down Initial rate of climb Time to 5,000 ft. (1 523 m) Time to 10,000 ft. 3 030 «)•.. Absolute ceiling Service ceiling Ceiling on one engine :—• At 3,750 lb. (1 700 kg) At 3,500 lb. (i 587 kg) At 3,250 1b. (1 473 kg) 114-147 m.p.h. (232-237 km'Ji) 127-130 m.p.h. (204-209 km'h) 122-125 m.p.h. 196-201 km'h) 12 gals. (54,5 I) per hour. 625 miles (1005 km) 885 miles (1 423 km) 295 yds. ± 30 yds. (270 m ± 28 m) 110 ft. ± 15 ft (33,5 m ± 4,5 m) 340 yds. ± 30 yds. (311 m ± 27,5 m) 1 in 10.5 1 in 8 875 ft./min. (4,47 mjsa) 6.8 min. 16.8 min. 18,100 ft. (5 510 m) 16,000 ft. (4 880 m) 3,800 ft. (1 160 m) 5,400 ft. (1 650 m) 7,400 ft. (2 260 m)
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