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Aviation History
1921
1921 - 0016.PDF
JANUARY 6, 1921 OIA 8-0 •. P: 6-01' AREA . 256 5a. FT. TAIL PLANE AREA 167 ELEVATOR .. 10 - PIN ..2 ) • 9 RUDDER (2) • 6 • •• ESTIMATED VVEIGHT 120 lbs. PROPOSED DESIGN FOR MAN-POWERED AEROPL/tNF. FIG.4. Fig. 4 : Proposed design for man-powered aeroplane " As regards external wing struts and wires, it is unlikelythat we could reduce the resistance of the struts by much, butitis probable that the resistance of the wires (about 30 lbs.out of the 68 for struts and wires) could be reduced by about 60 per cent., by improving the section of the wires, and buryingall the end fittings. This would reduce strut and wire drag from 68 lbs. to 50 lbs. " It is probable that the resistance of all the wires andnecessary pylons for the monoplane form, previously referred to, would not be greater than this biplane figure of 50 lbs.,but the wing structure weight would certainly go up. It is also quite conceivable that tapered cantilever wings mightbe used, with as low a lift/drag ratio as the biplane surface i.e., 18), and that the strut and wire drag could thereby bewashed out. But again it is quite certain that the weight of such wings would be greater than that of externally braced ones. The matter being so indeterminate therefore (particu-larly as we know little about the efficiency of full size wings and practically nothing about tapered wings), it is safestto say that the best we ought to expect is a reduction in drag of wings, struts and wires of about 28 lbs. " Now all these aerodynamic improvements are present-daypossibilities, and could all be on one and the same machine. On this ' perfected ' machine we should have the followingdrags, at 101 -3 m.p.h. :— Lbs. Body .. ..'••-:.'•.•"*••'••..• ••••*;' 125 •-".,-•••-- Landing gear .. .''. .. . . o Tail unit .. ..'*.. .. .. 39 ' ': Wings with external struts and wires .. 403 ','• - 567 * 5' 0"- 1 ! ENGINE SPACE SPEED MONOPLANE 3000 BHP - 54CYL5 ENGINE TOTAL VVEIGHT 10100 LBS. LENGTH . 32-0" SPAN . 26-0" WING AREA 90 5&- FT. CHORD. . 4'ir FIG.5. Fig. 5 : Proposed design for speed monoplane 16
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