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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 86: DATA SHEET No. 10. Weight of Aerodrome No. 5, 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. 10. Weight of Aerodrome No. 5, 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, 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.

  • * 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.