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Aviation History
1945
1945 - 2014.PDF
OCTOBER IITH, 1945 FLIGHT 397 There is ample room for luggage beneath the pilot's floor and over twice this amount in the aft compartment. The arrangement of the spar to cause the least incon- venience in the cabin is ingenious. The slim graceful lines of the Dove are clearly ap- parent in this general ar- rangement. The clean frontal aspect being marked. PERFORMANCE (Loaded to 8,000 Ib.) Maximum-level speed 218 m.p.h. Altitude for maximum level speed 7,200't. Recommended continuous cruising speed at :— Sea level ISO m.p.h. 5,D00ft 160 m.p.h. 10,000ft 170 m.p.h. Maximum cruising altitude ... 13,000ft. Rate of climb at sea level (using normal climb power) ... 850 ft./min. Service ceiling (where the rate of climb is 100 ft/min.) ... 21,500ft. Take-off :—Distance to 50ft. in -till air :— (1) At sea level (on grass surface) , ... 500 yd. (2) At 6,000ft. and 23 C. atmospheric temperature (20° C, above standard) (on grass) 700yd. (3) At sea level, on a hard runway, if one engine fails when commencing to climb 1,230 yd. Landing :— Distance from 50ft. in still air, at sea level ... ... ... 500 yd Performance on one engine (using normal climb power, with opposite airscrewfeathered). Rate of climb 120 ft./min. up to 7,000ft. Absolute ceiling 10,000'r. CRUISING at 5,000ft. Proportion of take-off power. 0.75 0.66 0/47 Cruising speed. m.p.h. 194 184 160 Miles/gall. 6.0 6.4 7.6 Payload with 500 miles still- air range. Ib. 1,575 1,615 1,700 Range with 1,700 Ib. payload. miles 395 420 500 I \ \ I \ *o n* tcr> OWXNC V * LOADING —<fi / / * / / / 300 100 OF MILES C£R ANNUM (Above) Direct operating cost, pence per ton-mileAssumed utilisation 1,000 hours per annum. (Left) Direct operating cost,pence per ton-mile. flaps are fabric covered, the latter being pneumatically operated. The tailplane and fin are metal covered unite of conventional design, whilst elevators and rudder are fabric-covered surfaces. Engines are the latest de Havilland Gipsy units bearing the designation Gipsy Queen 71 and drive de Havilland . Hydromatic constant-speed feathering and braking air- screws. Power plants are interchangeable port and star- board and are so arranged that one power plant complete with oil tank and oil cooler can be changed and replaced in less than two hours in the field. An oil dilution system for easy starting in Arctic conditions is incorporated, and priming is by a Ki-gass pump in the cockpit. The fuel system incorporates two three-way cocks and two fuel fil- ters which are so arranged that either (i) the two pairs of tanks alone feed their respective engines, or (ii) either ENGINE DATA Two de Havilland Gipsy Queen 71 engines : inverted air-coo'ed . ix-cylindcr. in-line, geared and supercharged. Power outputs (per engine) : Take-off and emergencies—330 B.H.P. at sea level, rising to 344 B.H.P. at 4,000ft. All-out level—305 B.H.P. at 6,200ft. Continuous climb (used for one-engine flight)—285 B.H.P. at 7,000ft. Maximum weak-mixture cruising—252 B.H.P. at 6,600ft. Recommended continuous cruising (for long overhaul periods)— ISO B.H.P. at sea level, rising to 170 B.H.P. at 12.000ft. engine can be cross feed from either pair of tanks, thus all the available fuel may be used in any condition. Each unit of the tricycle undercarriage is pneumatically retracted and the shock absorption system is a development of that inaugurated in the Mosquito, the shock absorber units being of the rubber-compression type. Main legs are interchangeable port and starboard and incorporate radius- rod components common to all three wheels. The nose wheel is fully castoring and is-automatically self centring for retraction; its tyre is a Marstrand double-track type. Emergency lowering of the undercarriage is by mechanical means. There are no hydraulics in the Dove, the only power services being electric and pneumatic. Elec tricity is supplied from two 24-volt, 750 watt engine-driven generators feeding two 12 volt 1000 1500 2000 2500 30 UTILISATION. HOURS PER ANNUM. •ragon Rapide. Direct operating*st £ per aircraft flying hour. IOO 200 JO» wo THOUSANDS Of MILES PER A*NUM Direct operating cost, pence peraircraft mile. DIMENSIONS Gross wing area Span Overall length Overall height—over rudder Height to top of engine nacelle Door and floor level height Clearance under fuselage Track—to centre line of wheels Overall width of undercarriage... LOADINGS Span 2.46 fb. /sq, ft. Wing ... 23.9 lb./»q. ft. Power (take-off) 12.1 fb./B.H.P. 335 -,q ft. 57ft. 39ft. 4in. 13ft. 5t9in. 2ft. Sin. lft.9in 13ft. 9in 14ft. 7in
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