The Project Gutenberg eBook of Langley Memoir on Mechanical Flight, Parts I and II, by S. P. (Samuel Pierpont) Langley and Charles M. (Charles Matthews) Manly

[p297]

DATA SHEETS.

DATA SHEET No. 1. Weight of Aerodrome No. 5, as photographed on May 11, 1896. Certified to by R. L. Reed, May 6, 1896.

Parts.	Sizes.		Weight.
Parts.	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.			2443
2 Engine, gears, shafts, etc.			1110
3 Pump, pump shaft			231
4 Hull covering			350
5 Gasoline tanks, valves			178
6 Smokestack			342
7 Float			275
8 Reel			77
9 Wing clamps, 235; clamp for guy-posts, 29			264
10 Other things, counter			75
11 Burners			360
12 Boilers			651
13 Separators, steam gauge, pipe to engine			540
14 Exhaust pipe			143
15
16
17 Wings (without clamp)			1950
18 Tail (without clamp)
19 Rudder			350
20 Guy sticks, each, 57			114
21 Propellers			800
22 Extra length of midrod, 308; drop piece for rudder, 40			348
23 Wood Bowsprit			74
24 Other things
25
26
27 Fuel (at starting flight)			200
28 Water (at starting flight)			900
29
30
31 Sundries unknown
32
33
34 Total flying weight			11,775	26
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.		2.6
40 Total area of horizontal tail . . . sq. ft.
41 Total area of rudder (vertical) . . . sq. ft.		6
42 Horse-power at brake. Horse-power by formula* .72		7
43 Minimum pressure during 40 secs. lift, 150 lbs.
44 Lift at pendulum (during 40 secs. absolute) 5772
45 Lift at pendulum (during 40 secs. in terms of wt.) 49%
46 Minimum pressure with which wheels turn, 10 lbs.
47 Position of center of pressure of wings† F. W., 1575; R. W., 1383.5
48 Time of getting up full steam, 1 minute
49
50 Curvature of wings, 1/11
51 Root angle of wings, 9°
52 Tip angle of wings, 9°
53 Position of wings, Front rib on F. W., 1607; R. W., 1415.5
54 How guyed
55
56
57
58 Position of tail
59 Angle of tail
60 Co-efficient elasticity of tail
61 Position of rudder, center, 1288.3; rear end, 1229.8
62 Line of thrust, 2500
63 Line of thrust, 1500 which is 9 cm. below the center of midrod
64 Center of gravity₁ of whole, 1497
65 Center of gravity₂ 2501, i. e., 1 cm. above line of thrust
66 Center of pressure₁ of whole estimate, 1498
67 Center of pressure₂, 2536
68
69
70
71
72

Parts. Remarks.

1 Front end of bowsprit, 1686.3.
2 Front end of midrod, 1611.6.
5 Front edge of F. W., 1607.
8 C. of P. on F. W., 1575.
11 Back edge of F. W., 1527.
14 Back edge of cross frame, 1509.
17 Line through center of propellers, 1500.
21 C. of G., 1497.
24 Front edge of R. W., 1415.5.
27 C. of P. on R. W., 1383.5.
30 End of mid-rod, 1360.5.
33 Front end of rudder, 1343.8.
36 Back edge of R. W., 1335.5.
39 Center of rudder, 1288.3.
41 Back end of rudder, 1229.8.

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.