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

[p304]

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.
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, 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.

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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.
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, bearing points for clutch. etc.			2867
2 Engine, gears, shafts, etc.			2867
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