◊[p297]DATA SHEETS.DATA SHEET No. 1.Weight of Aerodrome No. 5, as photographed on May 11, 1896. Certified to by R. L. Reed, May 6, 1896.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.24432 Engine, gears, shafts, etc.11103 Pump, pump shaft2314 Hull covering3505 Gasoline tanks, valves1786 Smokestack3427 Float2758 Reel779 Wing clamps, 235; clamp for guy-posts, 2926410 Other things, counter7511 Burners36012 Boilers65113 Separators, steam gauge, pipe to engine54014 Exhaust pipe143151617 Wings (without clamp)195018 Tail (without clamp)19 Rudder35020 Guy sticks, each, 5711421 Propellers80022 Extra length of midrod, 308; drop piece for rudder, 4034823 Wood Bowsprit7424 Other things252627 Fuel (at starting flight)20028 Water (at starting flight)900293031 Sundries unknown323334 Total flying weight11,7752635363738 Total area of support (not including tail) . . . sq. ft.6839 Total area of support in feet, divided by total flying weight in lbs.2.640 Total area of horizontal tail . . . sq. ft.41 Total area of rudder (vertical) . . . sq. ft.642 Horse-power at brake. Horse-power by formula* .72743 Minimum pressure during 40 secs. lift, 150 lbs.44 Lift at pendulum (during 40 secs. absolute) 577245 Lift at pendulum (during 40 secs. in terms of wt.) 49%46 Minimum pressure with which wheels turn, 10 lbs.47 Position of center of pressure of wings† F. W., 1575; R. W., 1383.548 Time of getting up full steam, 1 minute4950 Curvature of wings, 1/1151 Root angle of wings, 9°52 Tip angle of wings, 9°53 Position of wings, Front rib on F. W., 1607; R. W., 1415.554 How guyed55565758 Position of tail59 Angle of tail60 Co-efficient elasticity of tail61 Position of rudder, center, 1288.3; rear end, 1229.862 Line of thrust, 250063 Line of thrust, 1500 which is 9 cm. below the center of midrod64 Center of gravity1of whole, 149765 Center of gravity22501, i. e., 1 cm. above line of thrust66 Center of pressure1of whole estimate, 149867 Center of pressure2, 25366869707172Parts. Remarks.1 Front end of bowsprit, 1686.3.2 Front end of midrod, 1611.6.5 Front edge of F. W., 1607.8 C. of P. on F. W., 1575.11 Back edge of F. W., 1527.14 Back edge of cross frame, 1509.17 Line through center of propellers, 1500.21 C. of G., 1497.24 Front edge of R. W., 1415.5.27 C. of P. on R. W., 1383.5.30 End of mid-rod, 1360.5.33 Front end of rudder, 1343.8.36 Back edge of R. W., 1335.5.39 Center of rudder, 1288.3.41 Back end of rudder, 1229.8.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 end of bowsprit, 1686.3.2 Front end of midrod, 1611.6.5 Front edge of F. W., 1607.8 C. of P. on F. W., 1575.11 Back edge of F. W., 1527.14 Back edge of cross frame, 1509.17 Line through center of propellers, 1500.21 C. of G., 1497.24 Front edge of R. W., 1415.5.27 C. of P. on R. W., 1383.5.30 End of mid-rod, 1360.5.33 Front end of rudder, 1343.8.36 Back edge of R. W., 1335.5.39 Center of rudder, 1288.3.41 Back end of rudder, 1229.8.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.