NO. 3 



APPENDIX 



30] 



DATA SHEET No. 5. 



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



Certified to by Chas. M. Manly, Jun< '.". L899. 



1 Frame, including everything of metal, permanent md 



undetachable, B\ich as bed-plate, cross-rods foj the 

 support ol propellers, bearing points for clutch, etc.; 

 (bowsprit, 78g) 



2 Engine, gears, shafts, etc 



;; Pump. 123; pump shaft, 49 



4 Hull covering, including apron and piece behind sep: 01 



5 Gasoline and air tanks, 167, 174; air valve, 16 



6 Smokestack, 319; counter, 95; burner, 170 



7 Float 



8 Reel, with fork and Boat 



9 Wing clamps, 1S8; clamps for guy-posts, 24 



10 Boiler, 7i;i; steam gauge and connections, 7:i... 



11 Front bearing post, 75; clutch-post, 58 



12 Rear bearing points 



13 Separator and pipes leading to engines and pomp 



1 1 Drop piece for guv-posts, IS: for rudder, 55 



15 



16 



17 Wings (without clamp) 



is Tail (without clamp) 



19 Rudder 



20 Guy sticks 



21 Propellers 



22 Extra length of midrod 



23 w 1 bowsprit 



24 Other things 



25 



26 



Weight. 



including tail) q- ft 



feet, divided by total flying 



.sq. ft. 



27 Fuel (at starting lli-jlit I . 



28 V\ -iter (at starting flighl I. 



29 



SO 



"I Sundries unknown 



32 



33 



54 Total dying weight 



35 



36 



37 



55 Total area of Bupport I ii 'I 



39 Total area of support in 



weight in lbs 



40 Total area of horizontal tail 



41 Total area of rudder (vertical) •• 



42 Horse-power at brake Horse-power by formula 



43 ;••;•;•; 



44 Lift at pendulum (.luring one minute absolute) 



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



16 Minimum pressure with which wheels turn... 



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



48 



I I 



50 Curvature of wings. 1 in Is 



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 \ngle of tail, 7° 3d' 



60 ('.-efficient elasticity of tail, 1240 grammes at enter to 



i ii to tl." horizontal 



61 Position of rudder 



62 



63 Line of thrust. 1500 



64 enter of gravity] of whole 



65 Center of gravity? 



66 Center of pressure, of whole estimate 



67 Center of pressure. 



| 8861 



1. 1 



357 

 584 

 316 

 I 



212 

 S43 

 loo 

 165 

 502 

 75 



:;o;v 



323 

 106 



IV II 

 377 

 128 



176 

 1526 



11.94S 



64 



i 



69 

 70 

 71 



72 



I 



Ige "f cylindrical pari ol 

 float, 



Front end of midrod, 1613.7. 



i :. , dge of 1 W., If* 



C. oi P. on F. W.. 1563.7. 



i W.. 1616.7. 



Line through centi i [prop 

 1500. 



('. of G., 1484 I. 



i dge R. W. 

 . 1. . p. on R W 

 End of midrod, 1351.8. 

 Front end of ruddi 

 Back edge R. W.. 13 

 Center of rudder. 1279 i, 

 p.a. k end of rudder, 1221. 



' 11. P. = 



Rev. x diam. x pit ch ratio x thrust 

 33000 



t This is calculated on the ass ption thai tl nter otpl eh w^ *«!*'&*£• rt. »^ff^« ge 



Xir.rper'^io'.V",;'./: ■ ^ S&T&J2 S* - <- —U.l bu, h rear wing - smaller or Urg.r 



this efficiency is smaller or larger per unit of surface. 



