[p306]DATA SHEET No. 10.Weight of Aerodrome No. 5, Flat Wings and Pénaud Rudder. Certified to by Chas. M. Manly, July 27, 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, gears, shafts, etc. (such as guy-wires and turn buckles, 26g).33422 Engine.4763 Pump, 301; pump shaft, 55; support to pump, 33.3894 Hull covering: front, 47; sides, 92; top 46; small side pieces, 44.2295 Gasoline and air tanks, 167, 165; air valve, 18; netting, 30; piece rear of separator, 20.4006 Smokestack, 310; piece to protect midrod, 63.3737 Float, 290; drop piece for rudder, 57.3478 Reel, fork and float, 128; counter, 95.2239 Wing clamps, 202; guy-post clamps, 33.23510 Burner, 170; boiler 759.92911 Separator with tubes brazed to it.51312 Steam pipe, 87; steam gauge and connections, 81.16813 Exhaust pipe, 90; wooden plugs in nose of frame, 1010014 Upper front bearing point and clutch post.13615 Lower front bearing point, 84; lower rear bearing point, 146; clutch, 41.2711617 Wings (without clamp), front, 2 × 662; rear 2 × 605.253418 Tail (without clamp).19 Rudder.29920 Guy sticks 65; rear, 50.11421 Propellers, 100 cm. round ends, 30° blade.75722 Extra length of midrod, front, 174; rear, 227.40123 Wood bowsprit (heavy one).13024 Other things.252627 Fuel (390 at starting flight).22528 Water (2000 at starting flight).15002930 Lead on bowsprit to balance.1331 Sundries unknown.323334 Total flying weight.14,7041 0335363738 Total area of support (not including tail). . . . sq. ft.6839 Total area of support in feet, divided by total flying weight in lbs.2.193540 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 turn.47 Position of center of pressure of wings†.484950 Curvature of wings, 1 in 12, but about 1 in 11 now.51 Root angle of wings, 10°.52 Tip angle of wings 10°.53 Position of wings.54 How guyed.55565758 Position of tail.59 Angle of tail, 5° elevation at rear end.60 Co-efficient elasticity of tail, 200 grammes at center to deflect it to a horizontal.61 Position of rudder.6263 Line of thrust, 1500.64 Center of gravity1of whole, 1498.65 Center of gravity2.66 Center of pressure1of whole estimate.67 Center of pressure2.6869707172Parts. Remarks.1 Thirteen grammes of lead on end of bowsprit.2 End of bowsprit, 1708.4 C. of float, 1622.6 Front end of midrod, 1619.9 Reel and float, 1601.5.12 Front edge of F. W., 1609.7.15 C. of P. on F. W., 1577.7.17 Rear edge of F. W., 1529.7.20 Line through center of propellers, 150024 C. of G., 1498.27 Front edge of R. W., 1404.7.30 C. of P. on R. W., 1372.7.33 End of midrod, 1350.3.36 Front end of rudder, 1333.5.39 Back edge of R. W., 1324.7.41 Centre of rudder, 1279.5.44 Rear end of rudder, 1222.47 Distance between C. P. on F. W. and C. G., = 79.7. Distance between C. P. on R. W., and C. G. = 125.3. If the mean C. P. is to be over the C. G. we should require an efficiency of 63.6 for the rear wings.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 the rear wing is smaller or larger this efficiency is smaller or larger per unit of surface.
Parts. Remarks.1 Thirteen grammes of lead on end of bowsprit.2 End of bowsprit, 1708.4 C. of float, 1622.6 Front end of midrod, 1619.9 Reel and float, 1601.5.12 Front edge of F. W., 1609.7.15 C. of P. on F. W., 1577.7.17 Rear edge of F. W., 1529.7.20 Line through center of propellers, 150024 C. of G., 1498.27 Front edge of R. W., 1404.7.30 C. of P. on R. W., 1372.7.33 End of midrod, 1350.3.36 Front end of rudder, 1333.5.39 Back edge of R. W., 1324.7.41 Centre of rudder, 1279.5.44 Rear end of rudder, 1222.47 Distance between C. P. on F. W. and C. G., = 79.7. Distance between C. P. on R. W., and C. G. = 125.3. If the mean C. P. is to be over the C. G. we should require an efficiency of 63.6 for the rear wings.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 the rear wing is smaller or larger this efficiency is smaller or larger per unit of surface.
Parts. Remarks.
Footnotes.