[p307]DATA SHEET No. 11.Weight of Aerodrome No. 5, Superposed Wings and Pénaud Rudder. Certified to by Chas. M. Manly, August 3, 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.35562 Engine, complete4763 Pump, 301; pump shaft, 55; support to pump, 333894 Hull covering, 276; apron, 117; piece behind separator3935 Gasoline and air tanks, 167, 165; air valve, 173496 Smokestack and piece to protect midrod3857 Float, 290; drop piece for rudder, 57; guy-post and clamp, 173648 Reel, fork and float, 128; steam gauge with pipe, 812099 Wing claps, 202; guy-post clamps, 3323510 Boiler, 775; burner, 171; counter, 100104611 Rear extension to midrod22712 Separator and pipes to engine and pump51313 Exhaust pipe9014 Front lower bearing points, 84; clutch post, 4112515 Rear bearing points, 146; extra strengtheners, 321781617 Wings (without clamp)18 Tail (without clamp), part of rudder19 Rudder30920 Guy sticks, each 6012021 Propellers, 100 cm. round end75722 Extra length of midrod, front17423 Wood bowsprit13024 Other things, 248 grammes of lead on end of bowsprit248252627 Fuel (at starting flight)28 Water (at starting flight)293031 Sundries unknown323334 Total flying weight14,35435363738 Total area of support (not including tail) . . . sq. ft.87.539 Total area of support in feet, divided by total flying weight in lbs.2.7540 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 1151 Root angle of wings, 10°52 Tip angle of wings, 10°53 Position of wings54 How guyed55565758 Position of tail59 Angle of tail60 Co-efficient elasticity of tail, 200 grammes at center gives deflection of 5°61 Position rudder62 Elasticity caused by rubber bands63 Line of thrust, 150064 Center of gravity1of whole65 Center of gravity266 Center of pressure1of whole estimate67 Center of pressure26869707172Parts. Remarks.1 C. P. on F. W., 1577.7.2 Line through center of propellers, 1500.6 C. of G., 1498.8 C. P. on R. W., 1372.7.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.1 C. P. on F. W., 1577.7.2 Line through center of propellers, 1500.6 C. of G., 1498.8 C. P. on R. W., 1372.7.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.