NO. 3 



APPENDIX 



299 



DATA SHEET No. 3. 

 Weight of Aerodrome No. 6, Flat Wings and Penaud 1. 

 Certified to by ('has. M. Manly, June 7, L899. 



Frame, including everything of metal, permanent nnil 

 undetaehable, such as bed-plate, cross-rods tot thi 

 support of propellers, i for clutch, etc 



Engine, gears, shafts, etc 



Pump, 128; pump shaft, 4'' 



Hull covering, including apron and piece behind separal 



Gasoline and air tanks, 167, lit; air valve, 16 



Smokestack, 319; counter, 95; burner, 165 



Float, '27r>; pipe from pump to boiler, 40 



Reel, with fork and float 



Wing clamps, 188; guy-post clamps, 24 



Boiler. 764; steam cause and connections, 79 



Front lower bearing post, 75; clutch post, 5s ; rear bearing 

 points, 155 



Separator and pipes leading to engines and pomp 



Drop piece for rudder, 57; guy-post for rudder, is 



2 

 3 

 4 

 5 

 6 

 7 

 8 

 9 



10 



11 



12 

 13 



14 

 15 

 16 

 17 

 18 

 in 



20 

 21 

 22 

 23 

 24 

 25 

 26 

 27 





Wings (without clamp).... 



Supei posed wings, 3448 



Rudder ■ 



Guy sticks, each 53 



Propellers 



F.xtra length of midrod — 



Wood bowsprit 



Canvas keel, 30; rudder. 76. 



Fuel (at starting flight)... 

 Water (at starting flight). 



v,, ighl 



29 

 30 



31 Sundries unknown 



32 



34 Total flying weight. 



35 



37 



Total area of support (not including tail) sq. n 



39 Total area of support in feet, divided by total Hying 



wi ight in lbs •• 



40 Total area of horizontal tail "1 



41 Total area of rudder (vertical) ....sq.lt. 



42 Horse-power at brake Horse-power by formula 



43 



Curvature of wings. 1 in IS 



Root angle of wings, 10° 



Tip angle of wings, 10' 



Position of wings— front edge of front wing, 



rear wing, 1406.5 ■•■■, 



How guyed— with wires from wing to wing on top and 



to guy-post on bol torn 





41 Lift at pendulum (during one minute alio. Intel 



45 Lift at pendulum (during one minute in terms of wt.l... 



46 Minimum pressure with which wheels turn. ;■■-;■ 



47 Position of center of pressure of wings T 40% from front . 



4S 



49 

 50 

 51 

 52 

 53 



54 



55 

 56 

 57 

 58 

 59 

 60 

 6! 

 62 

 03 

 64 

 fir, 

 i a; 

 67 

 68 

 09 

 70 

 71 

 72 



2.04 



9.5 

 7 76 



Position of center of rudder, 1279.5. 



\ i . u i i of tail, 10° 



i o-efficient elasticity of tail 



I'o ii of rudder 



Line of thrust, 1500 



( enter of gravity] of whole, 1484.4 



i i M.r of gravitys 



Center of pressure, of whole estll 



Center of pressures 



2867 



172 

 274 

 297 

 579 

 315 

 128 

 212 

 si.; 



288 



602 



76 



2077 



323 

 100 

 620 

 377 

 128 

 112 



175 



15. -5 



11,995 



20.41 



Fronl (1 f bowsprit, li 

 Center of Boal 



i i. ,i,i edgi I mid I 



Center of II iat with small i • kt I 

 off, 1600 



Front edge of !'. w\. 1595 i 



C. of p. on F. W„ 



Bai I ■ ■!■ ■■■ I '< '■'■ ■ '<•' 



Line through i enter I 

 1500. 



C. of G., 1484.4. 



Froni edge of R. W., 140 



C. of P. on ft. W., 1374.5. 



F.nd of midrod, 1351.8. 

 Front end of rudder, 1335. 

 I edge of li. \\\. I 



i tenter of rudder, 1279.5. 

 Back end of rudder, 1221. 



' II. p. 



Rev , x diarn. x pit ch ratio x thrust 



■ 



t This is cal, alal d he ass ption that the center cypres* ., on »ch wing or onpair M ™jngs rt . ^*»» * 



%k I- Per^ace 5 S%?tZ I P^tear^o p' 



this effl. [i w | is smaller or larger per unit of surface. 



