[p303]DATA SHEET No. 7.Weight of Aerodrome No. 5, Flat Wings and Pénaud Rudder. Certified to by Chas. M. Manly, July 12, 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 gears, clutch, shafts, etc.30502 Engine4643 Pump, 334; pump shaft, with gear and eccentric and end rod, 553894 Hull Covering, 264; apron 115; piece behind separator, 193985 Gasoline and air tanks, 167, 165; air valve, 163486 Smokestack, 310; piece to protect midrod, 633737 Float, 275; drop piece for rudder, 57; guy-post, 183508 Reel, fork and float, 128; steam gauge with pipe, 812099 Wing clamps, 200; guy-post clamps, 3223210 Boiler, 764; burner, 170; counter, 95102911 Rear extension to midrod17412 Separator and pipes to engine and pump50213 Exhaust pipe, 848414 Front lower bearing point, 84; clutch post, 4112515 Rear bearing points, 146; extra strengtheners, 321781617 Wings (without clamp) (2180 in 1896)234218 Tail (without clamp); part of rudder19 Rudder reduced (No. 2 or new one, 299)32220 Guy sticks, each 5611221 Propellers (95 cms.; wood, 837; 95 cms. canvas, 548)83722 Extra length of midrod (front), 12912923 Wood bowsprit (complete), 13213224 Other things252627 Fuel (375 at starting flight)20028 Water (2100 at starting flight) + 616 in boiler1400293031 Sundries unknown323334 Total flying weight13,37935363738 Total area of support (not including tail) . . . sq. ft.6839 Total area of support in feet, divided by total flying weight in lbs.40 Total area of horizontal tail . . . sq. ft.6.9441 Total area of rudder (vertical) . . . sq. ft.7.6442 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†484950 Curvature of wings, 1 in 1251 Root angle of wings, 10°52 Tip angle of wings, 10°53 Position of wings54 How guyed55565758 Position of tail59 Angle of tail, 7° 30′60 Co-efficient elasticity of tail, 1240 grammes at center of rudder to bring it to a horizontal; 490 grammes at point same distance from front end of rudder as length of rudder of 1896, to bring to horizontal61 Position of rudder6263 Line of thrust, 150064 Center of gravity1of whole65 Center of gravity266 Center of pressure1of whole estimate67 Center of pressure26869707172Parts. Remarks.1 Front end of bowsprit, 1700.5. Front end of midrod 1611.5.3 Front edge of F. W., 1609.7.6 C. of P. on F. W., 1577.7.9 Rear edge of F. W., 1529.7.12 Line through center of propellers 1500.16 Front edge of R. W., 1411.7.19 C. of P. on R. W., 1379.7.22 End of midrod, 1360.3.25 Front end of rudder, 1343.5.28 Back edge of R. W., 1331.7.31 Center of rudder, 1288.34 Back end of rudder, 1229.5.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 a pair of wings at a motion of 2000 feet per minute is in ordinary curved wings 2-5 the way from the front to the rear, that for wings of usual size the rear wing 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.1 Front end of bowsprit, 1700.5. Front end of midrod 1611.5.3 Front edge of F. W., 1609.7.6 C. of P. on F. W., 1577.7.9 Rear edge of F. W., 1529.7.12 Line through center of propellers 1500.16 Front edge of R. W., 1411.7.19 C. of P. on R. W., 1379.7.22 End of midrod, 1360.3.25 Front end of rudder, 1343.5.28 Back edge of R. W., 1331.7.31 Center of rudder, 1288.34 Back end of rudder, 1229.5.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 a pair of wings at a motion of 2000 feet per minute is in ordinary curved wings 2-5 the way from the front to the rear, that for wings of usual size the rear wing 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.