NO. 3 



APPENDIX 



303 



DATA SHEET No. 7. 

 Weight of Aerodrome No. 5, Flat Wings and Penaud !;■ 

 Certified to by Chas. i\f. Manly, July L2, 1899. 



Pai r s. 



Frame, Including everything of metal, permanent and 

 undetachable, such as bed plate cross-rods for the 

 support of propellers, bearing points for gears, 

 shafts, etc 



£ng 



Pump, 334; pump shaft, with gear and eccentric band 

 and rod, 55 



Hull covering, 264; apron. 115; piece behind separator, 19.. 



Gasoline and air tanks, 1ST, 165; air valve, It; 



Smokestack, 310: piece to protect midrod 63 



Float, 275; drop piece for rudder, 57; guy-post, 18 



Reel, i"ii, and float, 128; steam gauge with pipe, 81.. .. 



win;;- rlamps, 200; guy-post clamps, 32 



Boiler, 7l>4; burner, 17"; counter, 95 



Rear extension to midrod 



Separator and pipes to engine and pump 



Exhaust pipe, *4 



Front lower bearing: point, S4 : clutch post, 41 



Kear bearing points, 146; extra strengthened, 32 



(without clamp) (2180 in 1896) 



Tail (without clamp): part of rudder 



Rudder reduced (No. "2 or new one, 299) 



Guy sticks, each 50 



Propellers (95 cms.: wood, 837; 95 cms. canvas. 



Extra length of midrod (front). 129 



wed bowsprit (complete), 132 . 



Other things 



548). 



Fuel (375 at starting flight) 



Watei (2100 at starting; flight) 4 616 in boiler. 



Sundries unknown 



34 Total living weight. 



35 



36 

 37 

 38 

 39 



61 



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



Total area of support in feet, divided by total flying 



weight in lbs 



Total area of horizontal tail s.| ft 



Total area of rudder (vertical ) s<| ft 



Horse-power at brake.... Horse-power by formula * 



Lift it pendulum (during one minute absolute) 



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



Minimum pressure with which wheels turn 



Position of center of pressure of wings t 



Curvature of wings, I in 12 

 Root anirle of wings, 10°... 

 Tip angle of wings. )o" .... 



Position of wings 



How guyed 



Position of tail 



\ngle of tail, 7° 30' 



Co -■■Hi. ieni elasticity of tail, 1240 grammes at center of 



rudder to bring it to a horizontal: 490 grammes at 



p.iint same distance from front end Of rudder is Length 



of rudd.r of !-■"'. to bring to horizontal 



Position of rudder 



63 Line of thrust. 1500 



64 Center of gravity, of whole 



65 Center of gravity 2 



or, ( lent er of pressut . ol wholi e timate 



67 Center of pressure-. 



68 



69 



70 



71 



72 



Sizes. 



Weight. 



68 



6.94 

 7.64 



8060 

 464 



:.|s 



SO 



■ 

 1029 



17) 

 502 

 84 

 125 



ITS 



2342 



822 

 112 



831 

 129 

 132 



200 



14IK) 



13,379 





•H. P. 



Rev, x diam. x pitch ratio ■: thrust 

 33000 



Front icd ol bowsprit, 

 Fronl . nd i f midrod, 1611.5. 

 1609.1 

 P I 



Re u i re of F. W., I 



I'd- through ' ntei 

 1500 



Fron) edge of u. w.. 1411.7. 



n i: v. . 

 i nd ol rnidror 



i !"l'l ■ ,.'l of i 



, . of If. W . 1 31.7. 

 1288. 

 Peek end of rud 



t This is calculated on the assumption thai the i enter of pressure on each wing or on parr of wings at a motion of 

 minutes in ordinary curved wings ! 5 the waj from front to rear, that r i tr wings have 2-3 of the 



effil i, „. v i ' . o," ' . - and that the I til proper bears no part of the weigh, : but if rear wing is smaller or larger 



this efficiency is smaller or larger per ur.it of surface. 



