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.
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DATA SHEET No. 4. Weight of Aerodrome No. 6, Superposed Wings and Pénaud Rudder. Certified to by Chas. M. Manly, June 13, 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. | 2867 | |||
| 2 Engine, gears, shafts, etc. | ||||
| 3 Pump, 123; pump shaft, 49 | 172 | |||
| 4 Hull covering, including apron and piece behind separator | 274 | |||
| 5 Gasoline and air tanks, 167, 114; air valve, 16 | 297 | |||
| 6 Smokestack, 319; counter, 95; burner, 170 | 584 | |||
| 7 Float | 315 | |||
| 8 Reel, with fork and float | 128 | |||
| 9 Wing clamps, 188; guy-post clamps, 24 | 212 | |||
| 10 Boiler, 764; steam gauge and connections, 79 | 843 | |||
| 11 Front bearing point, 75; clutch post, 58; rear bearing points, 155 | 288 | |||
| 12 Separator and pipes to engines and pump | 502 | |||
| 13 Drop piece and guy-post for rudder | 75 | |||
| 14 | ||||
| 15 | ||||
| 16 | ||||
| 17 Wings (without clamp), 2077; superposed wings | 3448 | |||
| 18 Tail (without clamp) | ||||
| 19 Rudder | 323 | |||
| 20 Guy sticks | 106 | |||
| 21 Propellers | 620 | |||
| 22 Extra length of midrod | 377 | |||
| 23 Wood bowsprit | 128 | |||
| 24 Canvas keel, 36 | 36 | |||
| 25 | ||||
| 26 | ||||
| 27 Fuel (at starting flight) | 175 | |||
| 28 Water (at starting flight) | 1525 | |||
| 29 | ||||
| 30 | ||||
| 31 Sundries unknown | ||||
| 32 | ||||
| 33 | ||||
| 34 Total flying weight | 13,275 | |||
| 35 | ||||
| 36 | ||||
| 37 | ||||
| 38 Total area of support (not including tail) . . . . . . sq. ft. | 87.4 | |||
| 39 Total area of support in feet, divided by total flying weight in lbs. | ||||
| 40 Total area of horizontal tail . . . . . . sq. ft. | 9.5 | |||
| 41 Total area of rudder (vertical) . . . . . . sq. ft. | 7.75 | |||
| 42 Horse-power at brake . . . Horse-power by formula* | ||||
| 43 | ||||
| 44 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†, 40% from front | ||||
| 48 | ||||
| 49 | ||||
| 50 Curvature of wings, 1 in 18 | ||||
| 51 Root angle of wings, 10° | ||||
| 52 Tip angle of wings, 10° | ||||
| 53 Position of wings—front edge of front wing, 159 | ||||
| 54 How guyed | ||||
| 55 | ||||
| 56 | ||||
| 57 | ||||
| 58 Position of tail | ||||
| 59 Angle of tail, 712° | ||||
| 60 Co-efficient elasticity of tail, 1240 grammes at center to deflect to the horizontal | ||||
| 61 Position of rudder | ||||
| 62 | ||||
| 63 Line of thrust, 1500 | ||||
| 64 Center of gravity1 of whole, 1484.4 | ||||
| 65 Center of gravity2 | ||||
| 66 Center of pressure1 of whole estimate | ||||
| 67 Center of pressure2 | ||||
| 68 | ||||
| 69 | ||||
| 70 | ||||
| 71 | ||||
| 72 | ||||
Parts. Remarks.
- 1 Front edge of bowsprit, 1702.7. Weight 2867 gm. includes parts 2.
- 2 Center of float without small wind vane rudder, 1666.1. (Center of float with wind vane rudder on, 1627.)
- 8 Front edge of midrod, 1613.7.
- 11 Front edge of F. W., 1585.
- 13 C. of P. on F. W., 1563.7.
- 16 Rear edge of F. W., 1531.7.
- 19 Line through center of propellers, 1500.
- 23 C. of G., 1484.4.
- 26 Front edge of R. W., 1395.8.
- 29 C. of P. on R. W., 1374.5.
- 32 End of midrod, 1351.8.
- 35 Front end of rudder, 1335.
- 38 Back edge of R. W., 1342.5.
- 40 Center of rudder, 1279.5.
- 43 Back end of rudder, 1221.
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.
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