NO. 



APPENDIX 



297 



DATA SHEET No. 1. 



Weight of Aerodrome No. 5, as photographed on Maj 11, L896. 



Certified to bj R. L. Reed, Ma\ 6, L896. 



I'arls. 





Weight. 



1 Frame, including everything 'if metal, permanent and 



undetachable, Buch as bed-plate, cross-rods for the 

 Buppori of propellers, bearing points for clutch, etc 



2 Engine, gears, shafts, etc 



3 Pump, pump shaft 



4 Hull covering 



5 Gasoline tanks, valves 



6 Smokestack 



7 Float 



8 Reel 



3 Wins clamps, 235; clamp for guy-posts, 29 



10 Other things, counter 



11 Burnere 



12 Boilers 



13 Separators, steam gauge, pipe to ,111:1110 



14 Exhaust pipe 



15 



16 



17 Wings (without clamp) 



18 Tail (without clamp) 



19 Rudder 



20 Guy sticks, each, 57 



21 Propellers 



22 Extra length of midrbd, 308; drop piece for rudder, 40 



23 Wood bowsprit 



24 Other things 



25 



26 



27 Fuel (at starting Bight) 



28 Water (at starting flight) 



29 



30 



31 Sundries unknown 



32 



33 



34 Total riving weight 



35 



36 



37 



38 Total area of support (n>>t including tail! sq it 



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



wiight in lbs ; 



40 Total area of horizontal tail sq.fi 



41 Total area of rudder (vertical) s.j. ft 



42 Horse-power at brake Horse-power by formula * ,72.. 



43 Minimum pressure during 40 sees. lift. 150 lbs 



44 Lift at pendulum (during 40 sees, absolute) 5772 



45 Lift at pendulum (during 40 sees, in terms of wt.) 49" . 



46 Minimum pressure with which wheels turn. 1" lbs 



47 Position of center of pressure of wings t F. W., 1575; 



R. W.. 13S3.:, 



48 Time of getting up full steam. 1 minute 



49 



50 Curvature of wings. 1/11 



61 Root angle of wings, 11 



52 Tip angle of wings, 9" 



53 Position of wings. Front rib on F. W.. 1607; R. W., 1415 5 



54 How guyed 



55 " 



56 



57 



58 Position of tail 



50 Ingle of tail 



60 To-efficient elasticity of tail • 



61 Position of rudder, center. 1288.3; rear end, 1229.8 



62 Line of thrust, 2500 ■ ■.•"•■« 



63 Line of thrust, 1500 which is 9 cm. below the center of 



midrod 



64 Center of gravity, of whole. 1107 



65 Center of gravity,, 2501, i. e.. 1 cm. above line of thrust . 



66 Center of pressure] of whole estimate, 1498 



67 Center of pressures, 2530 



68 



70 

 71 



72 



2443 

 11 in 

 2:11 

 350 

 178 

 343 



77 

 264 



76 

 360 

 661 

 640 

 143 



1950 



350 

 114 

 BOO 

 348 



74 



200 



900 



11,775 



; > 



Front end of boWBpril 

 i ol midr d, 



1 1 ,,i ed ;e of 1 SV., 16 

 • of P. on F. V, 

 Back edge of F, \\ , 



cross fri ', 1609. 



Line through 1 

 1500. 



c. of a., 1 



Fronl edge of It. W., 1415 5. 

 C. of P. on It. W.. 1383.5. 

 End of midi d 136 

 Front end of rudder, 1343.8. 

 Bai k edge of R. w., 1835 



t 1 uddi 1 ■ ! 

 Hark end of rudder, 1229.8. 



R ev, x diam . pitch ratio thrust 



thai the center of pressure on each wing or on pair of wtags al 1. mo 

 itetain ordinary curved wings •■ ° «ar, thai for wings of usual 



t This is calculated on tin as umption 



ir 01 wings ai a """ ' ■ 



,, wings have 2 •• ol the 



mimi . 



efficiency per surface of the front 



this efficiency is smaller or larger per unit of surface. 



I 5K Sr^"£»- i-t of the "weight; bul 1, rear w„,g is smal.er or larger 



