[p304]DATA SHEET No. 8.Weight of Aerodrome No. 5, Flat Wings and Pénaud Rudder. Certified to by Chas. M. Manly, July 19, 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, gears, shafts, etc.4763 Pump, pump shaft3894 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, 800; burner, 170; counter, 95106511 Rear extension to midrod17412 Separator and pipes to engine and pump50213 Exhaust pipe8414 Front lower bearing point, 84; clutch post, 4112515 Rear bearing points, 146; extra strengtheners, 321781617 Wings (without clamp)244618 Tail (without clamp), part of rudder19 Rudder29920 Guy sticks, each 5611221 Propellers, 95 cm. wood83722 Extra length of midrod16823 Wood bowsprit7824 Other things252627 Fuel (375 at starting flight)20028 Water (2100 at starting flight) + 616 in boiler1400293031 Sundries unknown323334 Total flying weight35363738 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.41 Total area of rudder (vertical) . . . sq. ft.42 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 wings51 Root angle of wings, 10°52 Tip angle of wings, 10°53 Position of wings54 How guyed55565758 Position of tail59 Angle of tail, 5°60 Co-efficient elasticity of tail, 200 grammes at center gives deflection to horizontal61 Position of rudder62 Elasticity caused by two 1/2-inch rubber bands above and two 1/4-inch bands, in tandem, below63 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, 1683.5.2 C. of float, 1614.5.5 Front end of midrod, 1611.5.8 C. of reel and float, 1577.5.11 Front edge of F. W., 1609.7.14 C. of P. on F. W., 1577.7.17 Rear edge of F. W., 1529.7.20 Line through center of propellers, 1500.24 C. of G., 1498.27 Front edge of R. W., 1406.7.30 C. of P. on R. W., 1374.7.33 End of midrod, 1360.3.36 Front end of rudder, 1343.5.39 Back edge of R. W., 1326.7.41 Center of rudder, 1288.44 Back end of rudder, 1229.5.47 N. B.—Distance between C. P. on F. W., and C. G. = 79.7. Distance between C. P. on R. W. and C. G. = 123.3. If the mean C. P. is to be over the C. G. we should require an efficiency for the rear wings of 64.6%.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 Front end of bowsprit, 1683.5.2 C. of float, 1614.5.5 Front end of midrod, 1611.5.8 C. of reel and float, 1577.5.11 Front edge of F. W., 1609.7.14 C. of P. on F. W., 1577.7.17 Rear edge of F. W., 1529.7.20 Line through center of propellers, 1500.24 C. of G., 1498.27 Front edge of R. W., 1406.7.30 C. of P. on R. W., 1374.7.33 End of midrod, 1360.3.36 Front end of rudder, 1343.5.39 Back edge of R. W., 1326.7.41 Center of rudder, 1288.44 Back end of rudder, 1229.5.47 N. B.—Distance between C. P. on F. W., and C. G. = 79.7. Distance between C. P. on R. W. and C. G. = 123.3. If the mean C. P. is to be over the C. G. we should require an efficiency for the rear wings of 64.6%.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.