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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 85: DATA SHEET No. 9. Weight of Aerodrome No. 6, Flat Wings and Pénaud Rudder. Certified to by Chas. M. Manly, July 27, 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. 9. Weight of Aerodrome No. 6, Flat Wings and Pénaud Rudder. Certified to by Chas. M. Manly, July 27, 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, 174; air valve, 18 361
6 Smokestack, 319; counter, 95; burner, 170 584
7 Float 290
8 Reel, 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 leading to engine and pump 502
13 Drop piece and guy-post for rudder 75
14
15
16
17 Wings (without clamp), repaired 2123
18 Tail (without clamp)
19 Rudder 299
20 Guy sticks 106
21 Propellers 628
22 Extra length of midrod 377
23 Wood bowsprit 78
24 Other things (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 12,019
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†
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, 5°
60 Co-efficient elasticity of tail, 200 grammes at center to deflect it 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 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.