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

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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.
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. (bowsprit, 78g)			2867
2 Engine, gears, shafts, etc.			2867
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 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 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.

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.