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Langley Memoir on Mechanical Flight, Parts I and II / Smithsonian Contributions to Knowledge, Volume 27 Number 3, Publication 1948, 1911 cover

Langley Memoir on Mechanical Flight, Parts I and II / Smithsonian Contributions to Knowledge, Volume 27 Number 3, Publication 1948, 1911

Chapter 80: DATA SHEET No. 4. Weight of Aerodrome No. 6, Superposed Wings and Pénaud Rudder. Certified to by Chas. M. Manly, June 13, 1899.
By S. P. Langley
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About This Book

The memoir chronicles systematic experimental work toward powered, heavier-than-air flight, presenting a chronological account of small flying models, aerodynamic tests with a whirling table, development of lightweight steam engines and launch apparatus. It explains why laboratory measurements differ from free-flight conditions, analyzes equilibrium and center-of-pressure issues, and records iterative trial-and-error design of wings, propellers, and supporting structures. Part of the text compiles detailed test data, field trial reports, and engineering challenges encountered during attempts to achieve sustained, controllable mechanical flight, with editorial additions completing later sections of the experimental record.

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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. 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, 159
54 How guyed
55
56
57
58 Position of tail
59 Angle of tail, 712°
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, 1484.4
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, 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.

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.