NO. 3 



APPENDI3 



30£ 



DATA SHEET No. f). 

 Weight of Aerodrome No. 6, Mat Wings and Pfoaud Ruddt 

 Certified to by Chas. M. Manly, July 27, 1899. 



Parts. 



Frame, including everything of metal, permanent and 

 undetachable, Buch as bed-plate, cross-rods foi thi 

 support of propellers, bearing points for clutch, etc .... 



Engine, gears, shafts, etc 



Pump, 123; pump shaft, (9 .....!! 



Hull covering, including apron and piece behind separate] 



Gasoline and air tanks, 167, 174; aii valve, 18... 



Smokestack, 319; counter, 95: burner, 170 



Float 



Reel, fork and float 



Wing .lamps, 1SS; guy-post clamps, 24 



Boiler, 764; steam gauge and connections, 79 



Front bearing point, TV, clutch post, 58; real bearing 



points, 155 



Separator and pipes leading to engine and pump 



Drop piece and guy-post for rudder 



Wings (without Clamp), repaired 



Tail (without clamp) 



Rudder 



Guy sticks 



Propellers 



Extra length of midrod 



Wood bowsprit 



Other things (canvas keel, 36; rudder. 76). 



Fuel (at starting Hiirht) 



Water (at starting flight). 



31 Sundries unknown 



32 



34 Total flying weight. 



35 



61 



Total area of support (riot including tail) sq.ft. 



Total area of support in feet, divided by total flying 



weight in lbs ." * 



Total area of horizontal t;iil sq. ft, 



Total area of rudder (vertical) sq. ft, 



Horse-power at brake Horse-power by formula " 



Sizea 



\\. ,: hi 



54 

 9.5 



Lift at pendulum (during one minute absolute) 



Lift at pendulum (during one minute in terms of wt.'i. 



Minimum pressure with which wheels turn 



Position of center of pressure of wings f 



Curvature of wings, 1 in 18. 

 Root angle of wings, tfl 



Tip angle of wings, 10° 



Position of wings 



How guyed 



Posil [on of tail 



Angle of tail, 5° 



Co-efficient elasticity of tail. 200 grammes al center to 



deflect it to the horizontal 



Position of rudder 



63 Line of thrust, 1500 



64 Center of gravity, of whole 



65 Center of gravity.. 



66 Center of pressure] of whole estimate. 



67 Center of pressure? 



69 

 70 

 71 



72 



Poundi 



2867 



r. ■ 



-'74 



684 

 280 

 128 

 212 

 843 



288 

 61 f 

 75 



299 

 106 



628 



877 



78 



112 



176 



1526 



12,019 



Remarks. 



Front end ol 



end of midrod, 1623.7. 

 ('. -if float, 1618.2. 

 Reel and float I 16 7. 

 If n< ■ dge I W.. 1595.8. 

 c. ol P. on F. w , I 

 R> Igi i w . 



Line through center ,.f propellers, 

 1600. 



C. of G., U85.5. 



Pronl edge ol K. W., 1406.7. 



C. of p. on R. W., 



End of midrod, 135 



Front end of rudder, 1333.9. 



Rear edu-c of K. W. , 



Center ol rudder, 1280.6. 



Back end „f rudder. 1219.9. 



' IT. r. = 



RV\ . - .fiiiiu. piteli ratio -Mn use 

 33KK1 



f This is calculated on the assumption that the center of pressure on each wing or on pair of wintrs at a motion ,.f 2000 reel per 

 minute is in ordinary curved wings 2-5 the waj from froni to rear, that for wings of usual size the rear wini of the 



efficiency per surface of the front ones and that the tail proper bears no pari ol the weight; bul if rear wing is smaller or larger 

 this efficiency ia smaller or larger per unit of surface. 



34 



