Langley Memoir on Mechanical Flight, Parts I and II / Smithsonian Contributions to Knowledge, Volume 27 Number 3, Publication 1948, 1911 - S. P. Langley; Charles M. Manly

Parts. Remarks.

1 Front end of bowsprit, 1695.7. Weight 2867 includes Parts 2.
2 Front end of midrod, 1623.7.
5 C. of float, 1618.2.
8 Reel and float, 1576.7.
11 Front edge, F. W., 1595.8.
13 C. of P. on F. W., 1563.8.
16 Rear edge F. W., 1515.8.
19 Line through center of propellers, 1500.
23 C. of G., 1485.5.
26 Front edge of R. W., 1406.7.
29 C. of P. on R. W., 1374.7.
32 End of midrod, 1352.2.
35 Front end of rudder, 1333.9.
38 Rear edge of R. W., 1326.7.
40 Center of rudder, 1280.6.
43 Back end of rudder, 1219.9.

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 the rear wing is smaller or larger this efficiency is smaller or larger per unit of surface.

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DATA SHEET No. 10. Weight of Aerodrome No. 5, Flat Wings and Pénaud Rudder. Certified to by Chas. M. Manly, July 27, 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, gears, shafts, etc. (such as guy-wires and turn buckles, 26g).			3342
2 Engine.			476
3 Pump, 301; pump shaft, 55; support to pump, 33.			389
4 Hull covering: front, 47; sides, 92; top 46; small side pieces, 44.			229
5 Gasoline and air tanks, 167, 165; air valve, 18; netting, 30; piece rear of separator, 20.			400
6 Smokestack, 310; piece to protect midrod, 63.			373
7 Float, 290; drop piece for rudder, 57.			347
8 Reel, fork and float, 128; counter, 95.			223
9 Wing clamps, 202; guy-post clamps, 33.			235
10 Burner, 170; boiler 759.			929
11 Separator with tubes brazed to it.			513
12 Steam pipe, 87; steam gauge and connections, 81.			168
13 Exhaust pipe, 90; wooden plugs in nose of frame, 10			100
14 Upper front bearing point and clutch post.			136
15 Lower front bearing point, 84; lower rear bearing point, 146; clutch, 41.			271
16
17 Wings (without clamp), front, 2 × 662; rear 2 × 605.			2534
18 Tail (without clamp).
19 Rudder.			299
20 Guy sticks 65; rear, 50.			114
21 Propellers, 100 cm. round ends, 30° blade.			757
22 Extra length of midrod, front, 174; rear, 227.			401
23 Wood bowsprit (heavy one).			130
24 Other things.
25
26
27 Fuel (390 at starting flight).			225
28 Water (2000 at starting flight).			1500
29
30 Lead on bowsprit to balance.			13
31 Sundries unknown.
32
33
34 Total flying weight.			14,704	1 03
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.		2.1935
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, but about 1 in 11 now.
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° elevation at rear end.
60 Co-efficient elasticity of tail, 200 grammes at center to deflect it to a horizontal.
61 Position of rudder.
62
63 Line of thrust, 1500.
64 Center of gravity₁ of whole, 1498.
65 Center of gravity₂.
66 Center of pressure₁ of whole estimate.
67 Center of pressure₂.
68
69
70
71
72

Parts. Remarks.

1 Thirteen grammes of lead on end of bowsprit.
2 End of bowsprit, 1708.
4 C. of float, 1622.
6 Front end of midrod, 1619.
9 Reel and float, 1601.5.
12 Front edge of F. W., 1609.7.
15 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., 1404.7.
30 C. of P. on R. W., 1372.7.
33 End of midrod, 1350.3.
36 Front end of rudder, 1333.5.
39 Back edge of R. W., 1324.7.
41 Centre of rudder, 1279.5.
44 Rear end of rudder, 1222.
47 Distance between C. P. on F. W. and C. G., = 79.7. Distance between C. P. on R. W., and C. G. = 125.3. If the mean C. P. is to be over the C. G. we should require an efficiency of 63.6 for the rear wings.

Footnotes.