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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 84: DATA SHEET No. 8. Weight of Aerodrome No. 5, Flat Wings and Pénaud Rudder. Certified to by Chas. M. Manly, July 19, 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. 8. Weight of Aerodrome No. 5, Flat Wings and Pénaud Rudder. Certified to by Chas. M. Manly, July 19, 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. 3556
2 Engine, gears, shafts, etc. 476
3 Pump, pump shaft 389
4 Hull covering, 264; apron, 115; piece behind separator, 19 398
5 Gasoline and air tanks, 167, 165; air valve, 16 348
6 Smokestack, 310; piece to protect midrod, 63 373
7 Float, 275; drop piece for rudder, 57; guy-post, 18 350
8 Reel, fork and float, 128; steam gauge with pipe, 81 209
9 Wing clamps, 200; guy-post clamps, 32 232
10 Boiler, 800; burner, 170; counter, 95 1065
11 Rear extension to midrod 174
12 Separator and pipes to engine and pump 502
13 Exhaust pipe 84
14 Front lower bearing point, 84; clutch post, 41 125
15 Rear bearing points, 146; extra strengtheners, 32 178
16
17 Wings (without clamp) 2446
18 Tail (without clamp), part of rudder
19 Rudder 299
20 Guy sticks, each 56 112
21 Propellers, 95 cm. wood 837
22 Extra length of midrod 168
23 Wood bowsprit 78
24 Other things
25
26
27 Fuel (375 at starting flight) 200
28 Water (2100 at starting flight) + 616 in boiler 1400
29
30
31 Sundries unknown
32
33
34 Total flying weight
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.
40 Total area of horizontal tail . . . sq. ft.
41 Total area of rudder (vertical) . . . sq. ft.
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
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 gives deflection to horizontal
61 Position of rudder
62 Elasticity caused by two 1/2-inch rubber bands above and two 1/4-inch bands, in tandem, below
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, 1683.5.
  • 2 C. of float, 1614.5.
  • 5 Front end of midrod, 1611.5.
  • 8 C. of reel and float, 1577.5.
  • 11 Front edge of F. W., 1609.7.
  • 14 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., 1406.7.
  • 30 C. of P. on R. W., 1374.7.
  • 33 End of midrod, 1360.3.
  • 36 Front end of rudder, 1343.5.
  • 39 Back edge of R. W., 1326.7.
  • 41 Center of rudder, 1288.
  • 44 Back end of rudder, 1229.5.
  • 47 N. B.—Distance between C. P. on F. W., and C. G. = 79.7. Distance between C. P. on R. W. and C. G. = 123.3. If the mean C. P. is to be over the C. G. we should require an efficiency for the rear wings of 64.6%.

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.