[p299]DATA SHEET No. 3.Weight of Aerodrome No. 6, Flat Wings and Pénaud Rudder. Certified to by Chas. M. Manly, June 7, 1899.Parts.Sizes.Weight.m.ft.gr.lbs.1 Frame, including everything of metal, permanent and undetachable, such as bed-plate, cross-rods for the support of propellers, bearing points for clutch, etc.28672 Engine, gears, shafts, etc.3 Pump, 123; pump shaft, 491724 Hull covering, including apron and piece behind separator2745 Gasoline and air tanks, 167, 114; air valve, 162976 Smokestack, 319; counter, 95; burner, 1656797 Float, 275; pipe from pump to boiler, 403158 Reel, with fork and float1289 Wing clamps, 188; guy-post clamps, 2421210 Boiler, 764; steam gauge and connections, 7984311 Front lower bearing post, 75; clutch post, 58; rear bearing points, 15528812 Separator and pipes leading to engines and pump50213 Drop piece for rudder, 57; guy-post for rudder, 187514151617 Wings (without clamp)207718 Superposed wings, 344819 Rudder32320 Guy sticks, each 5310621 Propellers62022 Extra length of midrod37723 Wood bowsprit12824 Canvas keel, 36; rudder, 76112252627 Fuel (at starting flight)17528 Water (at starting flight)1525293031 Sundries unknown323334 Total flying weight11,99526.4435363738 Total area of support (not including tail) . . . sq. ft.5439 Total area of support in feet, divided by total flying weight in lbs.2.0440 Total area of horizontal tail . . . sq. ft.9.541 Total area of rudder (vertical) . . . sq. ft.7.7542 Horse-power at brake . . . Horse-power by formula*4344 Lift at pendulum (during one minute absolute)45 Lift at pendulum (during one minute in terms of wt.)46 Minimum pressure with which wheels turn47 Position of center of pressure of wings† 40% from front484950 Curvature of wings, 1 in 1851 Root angle of wings, 10°52 Tip angle of wings, 10°53 Position of wings—front edge of front wing, 1595.7; of rear wing, 1406.554 How guyed—with wires from wing to wing on top and to guy-post on bottom55565758 Position of center of rudder, 1279.559 Angle of tail, 10°60 Co-efficient elasticity of tail61 Position of rudder6263 Line of thrust, 150064 Center of gravity1of whole, 1484.465 Center of gravity266 Center of pressure1of whole estimate67 Center of pressure26869707172Parts. Remarks.1 Front edge of bowsprit, 1702.7. Weight 2867 gm. for part 1 includes also part 2.2 Center of float with small wind vane rudder, 1628.9.6 Front edge of midrod, 1613.7.9 Center of float with small rudder off, 1609.2.12 Front edge of F. W., 1595.7.15 C. of P. on F. W., 1563.7.18 Back edge of F. W., 1515.7.21 Line through center of propellers, 1500.25 C. of G., 1484.4.28 Front edge of R. W., 1406.5.31 C. of P. on R. W., 1374.5.34 End of midrod, 1351.8.37 Front end of rudder, 1335.39 Back edge of R. W., 1326.5.42 Center of rudder, 1279.5.45 Back end of rudder, 1221.Footnotes.* H. P. = (Rev. × diam. × pitch ratio × thrust)/33000† This is calculated on the assumption that the center of pressure on each wing or on pair of wings at a motion of 2000 feet per minute is in ordinary curved wings 2-5 the way from front to rear, that for wings of usual size the rear wings have 2-3 of the efficiency per surface of the front ones and that the tail proper bears no part of the weight; but if rear wing is smaller or larger this efficiency is smaller or larger per unit of surface.
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Parts. Remarks.1 Front edge of bowsprit, 1702.7. Weight 2867 gm. for part 1 includes also part 2.2 Center of float with small wind vane rudder, 1628.9.6 Front edge of midrod, 1613.7.9 Center of float with small rudder off, 1609.2.12 Front edge of F. W., 1595.7.15 C. of P. on F. W., 1563.7.18 Back edge of F. W., 1515.7.21 Line through center of propellers, 1500.25 C. of G., 1484.4.28 Front edge of R. W., 1406.5.31 C. of P. on R. W., 1374.5.34 End of midrod, 1351.8.37 Front end of rudder, 1335.39 Back edge of R. W., 1326.5.42 Center of rudder, 1279.5.45 Back end of rudder, 1221.Footnotes.* H. P. = (Rev. × diam. × pitch ratio × thrust)/33000† This is calculated on the assumption that the center of pressure on each wing or on pair of wings at a motion of 2000 feet per minute is in ordinary curved wings 2-5 the way from front to rear, that for wings of usual size the rear wings have 2-3 of the efficiency per surface of the front ones and that the tail proper bears no part of the weight; but if rear wing is smaller or larger this efficiency is smaller or larger per unit of surface.
Parts. Remarks.
Footnotes.