- 1 Front end of midrod, 1611.5.
- 2 Front edge of F. W., 1609.7.
- 5 C. of P. on F. W., 1577.7.
- 8 Back edge of F. W., 1529.7.
- 11 Line through center of propellers, 1500.
- 15 C. of G., 1494.6.
- 18 Front edge of R. W., 1411.7.
- 21 C. of P. on R. W., 1379.7.
- 24 Rear end of midrod, 1360.3.
- 27 Rear end of R. W., 1331.7.
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.
[p303]
DATA SHEET No. 7. Weight of Aerodrome No. 5, Flat Wings and Pénaud Rudder. Certified to by Chas. M. Manly, July 12, 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 gears, clutch, shafts, etc. | 3050 | |||
| 2 Engine | 464 | |||
| 3 Pump, 334; pump shaft, with gear and eccentric and end rod, 55 | 389 | |||
| 4 Hull Covering, 264; apron 115; piece behind separator, 19 | 398 | |||
| 5 Gasoline and air tanks, 167, 165; air valve, 16 | 348 | |||
| 6 Smokestack, 310; piece to protect midrod, 63 | 373 | |||
| 7 Float, 275; drop piece for rudder, 57; guy-post, 18 | 350 | |||
| 8 Reel, fork and float, 128; steam gauge with pipe, 81 | 209 | |||
| 9 Wing clamps, 200; guy-post clamps, 32 | 232 | |||
| 10 Boiler, 764; burner, 170; counter, 95 | 1029 | |||
| 11 Rear extension to midrod | 174 | |||
| 12 Separator and pipes to engine and pump | 502 | |||
| 13 Exhaust pipe, 84 | 84 | |||
| 14 Front lower bearing point, 84; clutch post, 41 | 125 | |||
| 15 Rear bearing points, 146; extra strengtheners, 32 | 178 | |||
| 16 | ||||
| 17 Wings (without clamp) (2180 in 1896) | 2342 | |||
| 18 Tail (without clamp); part of rudder | ||||
| 19 Rudder reduced (No. 2 or new one, 299) | 322 | |||
| 20 Guy sticks, each 56 | 112 | |||
| 21 Propellers (95 cms.; wood, 837; 95 cms. canvas, 548) | 837 | |||
| 22 Extra length of midrod (front), 129 | 129 | |||
| 23 Wood bowsprit (complete), 132 | 132 | |||
| 24 Other things | ||||
| 25 | ||||
| 26 | ||||
| 27 Fuel (375 at starting flight) | 200 | |||
| 28 Water (2100 at starting flight) + 616 in boiler | 1400 | |||
| 29 | ||||
| 30 | ||||
| 31 Sundries unknown | ||||
| 32 | ||||
| 33 | ||||
| 34 Total flying weight | 13,379 | |||
| 35 | ||||
| 36 | ||||
| 37 | ||||
| 38 Total area of support (not including tail) . . . sq. ft. | 68 | |||
| 39 Total area of support in feet, divided by total flying weight in lbs. | ||||
| 40 Total area of horizontal tail . . . sq. ft. | 6.94 | |||
| 41 Total area of rudder (vertical) . . . sq. ft. | 7.64 | |||
| 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† | ||||
| 48 | ||||
| 49 | ||||
| 50 Curvature of wings, 1 in 12 | ||||
| 51 Root angle of wings, 10° | ||||
| 52 Tip angle of wings, 10° | ||||
| 53 Position of wings | ||||
| 54 How guyed | ||||
| 55 | ||||
| 56 | ||||
| 57 | ||||
| 58 Position of tail | ||||
| 59 Angle of tail, 7° 30′ | ||||
| 60 Co-efficient elasticity of tail, 1240 grammes at center of rudder to bring it to a horizontal; 490 grammes at point same distance from front end of rudder as length of rudder of 1896, to bring to horizontal | ||||
| 61 Position of rudder | ||||
| 62 | ||||
| 63 Line of thrust, 1500 | ||||
| 64 Center of gravity1 of whole | ||||
| 65 Center of gravity2 | ||||
| 66 Center of pressure1 of whole estimate | ||||
| 67 Center of pressure2 | ||||
| 68 | ||||
| 69 | ||||
| 70 | ||||
| 71 | ||||
| 72 | ||||
Parts. Remarks.
- 1 Front end of bowsprit, 1700.5. Front end of midrod 1611.5.
- 3 Front edge of F. W., 1609.7.
- 6 C. of P. on F. W., 1577.7.
- 9 Rear edge of F. W., 1529.7.
- 12 Line through center of propellers 1500.
- 16 Front edge of R. W., 1411.7.
- 19 C. of P. on R. W., 1379.7.
- 22 End of midrod, 1360.3.
- 25 Front end of rudder, 1343.5.
- 28 Back edge of R. W., 1331.7.
- 31 Center of rudder, 1288.
- 34 Back end of rudder, 1229.5.
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 a pair of wings at a motion of 2000 feet per minute is in ordinary curved wings 2-5 the way from the front to the rear, that for wings of usual size the rear wing 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.