[p298]DATA SHEET No. 2.Weight of Aerodrome No. 6. Certified to by R. L. Reed, November 27 and 28, 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.11782 Engine, gears, shafts, etc.10433 Pump, pump shaft1904 Hull covering3455 Gasoline tanks, valves3066 Smokestack, 302; burner, 1724747 Float2758 Reel779 Wing clamps, 238; drop piece for rudder, 4027810 Other things15611 Boiler, frames, mica cover69412 Separator, steam gauge, pipe to engines53513 Exhaust pipe8214151617 Wings (without clamp), wet215418 Tail (without clamp)19 Rudder37520 Guy sticks, each 5310621 Propellers64422 Extra length of midrod39823 Wood bowsprit13524 Counter75252627 Fuel (at starting flight)25028 Water (at starting flight)2350293031 Sundries unknown323334 Total flying weight12,12035363738 Total area of support (not including tail) . . . sq. ft.5439 Total area of support in feet, divided by total flying weight in lbs.240 Total area of horizontal tail . . . sq. ft..641 Total area of rudder (vertical) . . . sq. ft..642 Horse-power at brake. . .Horse-power by formula*43 Minimum steam pressure during 40 secs. lift13044 Lift at pendulum (during one minute absolute)7,21145 Lift at pendulum (during one minute in terms of wt.)46 Minimum pressure with which wheels turn1047 Position of center of pressure of wings†48 Time of getting up full steam, 75 secs.49 Angle of midrod with horizon, 2° 17′50 Curvature of wings, 1 in 18, 1/4 from front51 Root angle of wings, 10° 30′52 Tip angle of wings, 10° 30′53 Position of wings54 How guyed55565758 Position of tail59 Angle of tail60 Co-efficient elasticity of tail61 Position of rudder6263 Line of thrust 150064 Center of gravity1of whole, 1483.865 Center of gravity2, 2482‡66 Center of pressure1of whole estimate, 148767 Center of pressure2, 25206869707172Parts. Remarks.1 Front end of bowsprit, 1797.2 Center of float in first trial, Nov.6 Front end of midrod, 1613.7. 9 Front edge of F. W., 1595.7.12 Center of float in flight, Nov. 28, 1896, 1575.8.16 C. of P. on F. W., 1563.7.19 Back edge of F. W., 1515.7.22 Line through centerof propellers, 1500.26 C. of G., 1484.4 (old C. of G., 1486.3).29 Front edge of R. W., 1406.32 C. of P. on R. W., 1374.35 End of midrod, 1351.338 Front end of rudder, 1334.5.41 Back edge of R. W., 1326.43 Center of rudder, 1279.46 Back end of rudder, 1220.5.49 Reed wings, 80 cm. × 185 cm. in rectangle.53 Weight in shop, 1982 g.56 On day of flight they weighed 2154 g. because they were damp.60 Area 54 sq. ft.63 Spread of wings, 359 cms. or 11′938″.67 Weight of aerodrome in flight, 12,120 grs.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.‡ This is undoubtedly incorrect, as if it were true, the C. G. would be just at the center of the separator, and this would be impossible. Mr. Reed states that the C. G. was 2 cm. below the side frame, and if this is correct, we would have C. G. = 2486.
[p298]
Parts. Remarks.1 Front end of bowsprit, 1797.2 Center of float in first trial, Nov.6 Front end of midrod, 1613.7. 9 Front edge of F. W., 1595.7.12 Center of float in flight, Nov. 28, 1896, 1575.8.16 C. of P. on F. W., 1563.7.19 Back edge of F. W., 1515.7.22 Line through centerof propellers, 1500.26 C. of G., 1484.4 (old C. of G., 1486.3).29 Front edge of R. W., 1406.32 C. of P. on R. W., 1374.35 End of midrod, 1351.338 Front end of rudder, 1334.5.41 Back edge of R. W., 1326.43 Center of rudder, 1279.46 Back end of rudder, 1220.5.49 Reed wings, 80 cm. × 185 cm. in rectangle.53 Weight in shop, 1982 g.56 On day of flight they weighed 2154 g. because they were damp.60 Area 54 sq. ft.63 Spread of wings, 359 cms. or 11′938″.67 Weight of aerodrome in flight, 12,120 grs.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.‡ This is undoubtedly incorrect, as if it were true, the C. G. would be just at the center of the separator, and this would be impossible. Mr. Reed states that the C. G. was 2 cm. below the side frame, and if this is correct, we would have C. G. = 2486.
Parts. Remarks.
Footnotes.