Chapter XXXIV: Appendix: Study of the American Buzzard and the “john Crow” (2)

---------------------------------------+----------+-------------+ 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, 165 | | | 679| | | | | | | 7 Float, 275; pipe from pump to | | | | | boiler, 40 | | | 315| | | | | | | 8 Reel, with fork and float | | | 128| | | | | | | 9 Wing clamps, 188; guy-post clamps, | | | 212| | 24 | | | | | | | | | | 10 Boiler, 764; steam gauge and | | | | | connections, 79 | | | 843| | | | | | | 11 Front lower bearing post, 75; | | | | | clutch post, 58; rear bearing points, | | | 288| | 155 | | | | | | | | | | 12 Separator and pipes leading to | | | | | engines and pump | | | 502| | | | | | | 13 Drop piece for rudder, 57; | | | 75| | guy-post for rudder, 18 | | | | | | | | | | 14 | | | | | | | | | | 15 | | | | | | | | | | 16 | | | | | | | | | | 17 Wings (without clamp) | | | 2077| | | | | | | 18 Superposed wings, 3448 | | | | | | | | | | 19 Rudder | | | 323| | | | | | | 20 Guy sticks, each 53 | | | 106| | | | | | | 21 Propellers | | | 620| | | | | | | 22 Extra length of midrod | | | 377| | | | | | | 23 Wood bowsprit | | | 128| | | | | | | 24 Canvas keel, 36; rudder, 76 | | | 112| | | | | | | 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 | | |11,995| 26.44| | | | | | 35 | | | | | | | | | | 36 | | | | | | | | | | 37 | | | | | | | | | | 38 Total area of support (not | | | | | including tail) sq. ft. | |54 | | | | | | | | 39 Total area of support in feet, | | | | | divided by total flying weight in lbs. | | 2.04| | | | | | | | 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, 1595.7; of rear wing, | | | | | 1406.5 | | | | | | | | | | 54 How guyed--with wires from wing to | | | | | wing on top and to guy-post on bottom | | | | | | | | | | 55 | | | | | | | | | | 56 | | | | | | | | | | 57 | | | | | | | | | | 58 Position of center of rudder, | | | | | 1279.5 | | | | | | | | | | 59 Angle of tail, 10° | | | | | | | | | | 60 Co-efficient elasticity of tail | | | | | | | | | | 61 Position of rudder | | | | | | | | | | 62 | | | | | | | | | | 63 Line of thrust, 1500 | | | | | | | | | | 64 Center of gravity_1 of whole, | | | | | 1484.4 | | | | | | | | | | 65 Center of gravity_2 | | | | | | | | | | 66 Center of pressure_1 of whole | | | | | estimate | | | | | | | | | | 67 Center of pressure_2 | | | | | | | | | | 68 | | | | | | | | | | 69 | | | | | | | | | | 70 | | | | | | | | | | 71 | | | | | | | | | | 72 | | | | |

Parts. Remarks.

1 Front edge of bowsprit, 1702.7. Weight 2867 gm. for part 1 includes also part 2.

2 Center of float with small wind vane rudder, 1628.9.

6 Front edge of midrod, 1613.7.

9 Center of float with small rudder off, 1609.2.

12 Front edge of F. W., 1595.7.

15 C. of P. on F. W., 1563.7.

18 Back edge of F. W., 1515.7.

21 Line through center of propellers, 1500.

25 C. of G., 1484.4.

28 Front edge of R. W., 1406.5.

31 C. of P. on R. W., 1374.5.

34 End of midrod, 1351.8.

37 Front end of rudder, 1335.

39 Back edge of R. W., 1326.5.

42 Center of rudder, 1279.5.

45 Back end of rudder, 1221.

* 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.

[p300]

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. | | 9.5 | | | ft. | | | | | | | | | | 41 Total area of rudder (vertical) | | 7.75| | | sq. ft. | | | | | | | | | | 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, 7-1/2° | | | | | | | | | | 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 gravity_1 of whole, | | | | | 1484.4 | | | | | | | | | | 65 Center of gravity_2 | | | | | | | | | | 66 Center of pressure_1 of whole | | | | | estimate | | | | | | | | | | 67 Center of pressure_2 | | | | | | | | | | 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.

* 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.

[p301]

DATA SHEET No. 5.

Weight of Aerodrome No. 6, Flat Wings and Pénaud Rudder. Certified to by Chas. M. Manly, June 22, 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. (bowsprit, 78g) | | | 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, 174; | | | | | air valve, 16 | | | 357| | | | | | | 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 post, 75; | | | | | clutch-post, 58 | | | 133| | | | | | | 12 Rear bearing points | | | 155| | | | | | | 13 Separator and pipes to engines and | | | | | pump | | | 502| | | | | | | 14 Drop piece and guy-posts, 18; for | | | | | rudder, 57 | | | 75| | | | | | | 15 | | | | | | | | | | 16 | | | | | | | | | | 17 Wings (without clamp) | | | 2077| | | | | | | 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 Other things | | | | | | | | | | 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 | | |11,948| 26.3 | | | | | | 35 | | | | | | | | | | 36 | | | | | | | | | | 37 | | | | | | | | | | 38 Total area of support (not | | | | | including tail) sq. ft. | |54 | | | | | | | | 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 | | | | | | | | | | 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 to deflect to | | | | | the horizontal | | | | | | | | | | 61 Position of rudder | | | | | | | | | | 62 | | | | | | | | | | 63 Line of thrust, 1500 | | | | | | | | | | 64 Center of gravity_1 of whole | | | | | | | | | | 65 Center of gravity_2 | | | | | | | | | | 66 Center of pressure_1 of whole | | | | | estimate | | | | | | | | | | 67 Center of pressure_2 | | | | | | | | | | 68 | | | | | | | | | | 69 | | | | | | | | | | 70 | | | | | | | | | | 71 | | | | | | | | | | 72 | | | | | ---------------------------------------+----+-----+------+------+

Parts. Remarks.

1 Front edge of bowsprit, 1685.7. Weight 2867 gm. includes Parts 2.

2 Back edge of cylindrical part of float, 1606.5

5 Front edge of midrod, 1613.7.

8 Front edge of F. W., 1595.7.

11 C. of P. on F. W., 1563.7.

14 Back edge of F. W., 1515.7.

17 Line through center of propellers, 1500.

21 C. of G., 1484.4.

24 Front edge R. W., 1406.5.

27 C. of P. on R. W., 1374.5.

30 End of midrod, 1351.8.

33 Front end of rudder, 1335.

36 Back edge R. W., 1326.5.

38 Center of rudder, 1279.5.

41 Back end of rudder, 1221.

* 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.

[p302]

DATA SHEET No. 6.

Weight of Aerodrome No. 5, Flat Wings and Pénaud Rudder. Certified to by Chas. M. Manly, June 23, 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. | | | 3050| | | | | | | 2 Engine | | | 464| | | | | | | 3 Pump, 334; pump shaft, 55 | | | 389| | | | | | | 4 Hull covering | | | 398| | | | | | | 5 Gasoline tanks, air tanks, valves, | | | | | etc. | | | 348| | | | | | | 6 Smokestack | | | 373| | | | | | | 7 Float, 275; drop piece for rudder, | | | | | 57; guy-post, 18 | | | 350| | | | | | | 8 Reel, 128; steam gauge, 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| | | | | | | 14 Front lower bearing point, 84; | | | | | clutch post, 41 | | | 125| | | | | | | 15 Rear bearing points, 146; extra | | | | | strengtheners, 32 | | | 178| | | | | | | 16 | | | | | | | | | | 17 Wings (without clamp) | | | 2342| | | | | | | 18 Tail (without clamp) | | | | | | | | | | 19 Rudder | | | 322| | | | | | | 20 Guy sticks, each 56 | | | 112| | | | | | | 21 Propellers | | | 837| | | | | | | 22 Extra length of midrod at front | | | 129| | | | | | | 23 Wood bowsprit | | | 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 | | |13,370| | | | | | | 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 | | | | | | | | | | 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 | | | | | | | | | | 61 Position of rudder | | | | | | | | | | 62 | | | | | | | | | | 63 Line of thrust, 1500 | | | | | | | | | | 64 Center of gravity_1 of whole | | | | | | | | | | 65 Center of gravity_2 | | | | | | | | | | 66 Center of pressure_1 of whole | | | | | estimate | | | | | | | | | | 67 Center of pressure_2 | | | | | | | | | | 68 | | | | | | | | | | 69 | | | | | | | | | | 70 | | | | | | | | | | 71 | | | | | | | | | | 72 | | | | | ---------------------------------------+----+-----+------+------+

Parts. Remarks.

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.

* 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. | | 6.94| | | ft. | | | | | | | | | | 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 gravity_1 of whole | | | | | | | | | | 65 Center of gravity_2 | | | | | | | | | | 66 Center of pressure_1 of whole | | | | | estimate | | | | | | | | | | 67 Center of pressure_2 | | | | | | | | | | 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.

* 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.

[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. | | | 3556 | | | | | | | 2 Engine, gears, shafts, etc. | | | 476 | | | | | | | 3 Pump, pump shaft | | | 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, 800; burner, 170; counter, | | | | | 95 | | | 1065 | | | | | | | 11 Rear extension to midrod | | | 174 | | | | | | | 12 Separator and pipes to engine and | | | | | pump | | | 502 | | | | | | | 13 Exhaust pipe | | | 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) | | | 2446 | | | | | | | 18 Tail (without clamp), part of | | | | | rudder | | | | | | | | | | 19 Rudder | | | 299 | | | | | | | 20 Guy sticks, each 56 | | | 112 | | | | | | | 21 Propellers, 95 cm. wood | | | 837 | | | | | | | 22 Extra length of midrod | | | 168 | | | | | | | 23 Wood bowsprit | | | 78 | | | | | | | 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 | | | | | | | | | | 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. | | | | | | | | | | 41 Total area of rudder (vertical) | | | | | sq. ft. | | | | | | | | | | 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 | | | | | | | | | | 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, 5° | | | | | | | | | | 60 Co-efficient elasticity of | | | | | tail, 200 grammes at center gives | | | | | deflection to horizontal | | | | | | | | | | 61 Position of rudder | | | | | | | | | | 62 Elasticity caused by two 1/2-inch | | | | | rubber bands above and two 1/4-inch | | | | | bands, in tandem, below | | | | | | | | | | 63 Line of thrust, 1500 | | | | | | | | | | 64 Center of gravity_1 of whole | | | | | | | | | | 65 Center of gravity_2 | | | | | | | | | | 66 Center of pressure_1 of whole | | | | | estimate | | | | | | | | | | 67 Center of pressure_2 | | | | | | | | | | 68 | | | | | | | | | | 69 | | | | | | | | | | 70 | | | | | | | | | | 71 | | | | | | | | | | 72 | | | | | ---------------------------------------+----+-----+------+------+

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%.

* 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.

[p305]

DATA SHEET No. 9.

Weight of Aerodrome No. 6, Flat Wings and Pénaud Rudder. Certified to by Chas. M. Manly, July 27, 1899.