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Aviation History
1931
1931 - 0598.PDF
SUPPLEMENT TOFLIGHT 44 THE AIRCRAFT ENGINEER JUNE 19, 1931 22 20 IS 16 14 12 10 8 6 4 2 \r r 1 0 L FIXEC \ * \ \ WIN( VARI V. w \ ABLE V\ 2 3 -4 •! *L :AMB( N\\ N > >£ R WIK \ a FIG.9 \ •7 -8 -9 600 500 400 300 IrtA HP 0 1 \ FIXED •^^ wir WINS AlRCF k RIABLE CAM>I6 AIRCRAF ^— f//V FIG.IO / V ) SO 80 100 120 140 160 180 V M.P.H greater clearance between the wheels and bottom plane, to be on the safe side, no advantage has been taken of these indications of reduced drag coefficients in favour of the V.C.W. alternative. The performances at sea level of the alternative machines are shown superposed on Fig. 10, while the performance particulars with respect to height are shown graphically by Figs. 11 and 12. The following table summarises the leading par- ticulars of these alternative aircraft: — Span (both planes) Overall lengthOverall height Chord Main plane areaTotal weight fully loaded Wing loading Span!* WAirscrew diameter Speed at 6.1. Speed at 5,000 ft.Speed at 10,000 ft. Speed at 16,000 ft.Rate of climb at s.I. Itate of climb, 10,000 ft.Time to 10,000 ft. Service celling Absolute ceiling .,Alighting speed Fixed WitvAircraft. . 44 It . 86 ft. 6 In. ... 12 ft. B in. . 7 ft. Ota.. 802 BO. ft.. 5,8601b. . 9-71b./Bq. ft. . 0-881 .. . lift . 165 in.ph. . 104 m.p.h.. 162 m.p.h. . 165-8 m.p.h. ... 1,180 ft. per min. . 560 ft. per min.. 12-6 min. . 19,000 ft. . 21,000 ft.. 56 m.p.h. Variable CamberWinff Aircraft. 41 ft;e m. 32 ft .3 In.11 ft .6 in. 5 ft. 3 lu.401 sq. ft. 5,5001b. 13-7 lb./sq.ft. 0-818 10 ft. 6 in. 177-5 m.p.h. 176-7 m.p.h.174 m.p.h. 168 m.p.h.1,250 ft. per min. 640 ft. per min.11-2 min. 20,250 ft. 22.200 ft.66 m.p.h. • The span loading in more favourable to the F.W. than to the V.C.W.aircraft. Apart from the higher performance of the V.C.W. machine, the following advantages are naturally obtained from this design: — (1) Smaller overall dimensions. (2) Improved manoeuvrability on account of the de- creased moments of inertia of the aircraft about all three axes. (3) Pilot's view greatly improved, not only because of the narrower top and bottom wing chords, but because the smaller gap enables the top wing to be placed at such a position relative to the cockpit that the edge view only is visible to the pilot. (4) Reduced fuel consumption. (In the example chosen this amounts to 11.5 per cent.) As time goes on the need for the adoption of variable lift devices becomes more and more apparent, since increased performances and greater useful loads are continually being demanded. Substantial advantages may be obtained in practically every type of aircraft, and the application of variable camber, already in an advanced state of development, is susceptible of still further improvements regarding such matters as effective lateral control and simplicity of design. The author wishes to acknowledge his indebtedness to the Controller of H.M. Stationery Office and to the Secretary of the Aeronautical Research Committee in connection with the preparation of this article. 25000 20000 15000 VARIABLE CAMBER WING AIRCRAFT \ 10000 5000 RATE OF CLIMB VIIN 200 TIME TO HEIGHT MIN K> 400 20 600 30 800 40 1000 50 1200 60 100 120 140 SPEED M.P.H 556d
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