300 



SMITHSONIAN CMX'l KII'.I'TIO.NS To KNOWLEDGE 



vol. 27 



DATA SHEET No. 4. 



Weigh) of \ Irome No. 6, Superposed \\ ings and Penaud Rudder. 



Certified to by ('lias. M. Manly, June 13, 1899. 



Parts. 



1 Frame, including everything of metal, permanent and 



undetachable, such as bed-plate, cross-rods for tin 

 support of pi bearing points for clutch, etc 



2 Engine, gears, bafts, etc 



:: Pump, 123; pump 



4 Hull covering, im ' tnd i ei i behind separator. 



tanks, 167, 111; air valve, 16 



319; counter, 95; burner, 17o 



; Float 



9 



10 

 11 



12 

 13 



14 

 15 

 16 



II 

 18 

 l I 

 I 

 21 

 22 

 23 

 24 

 25 

 26 



28 

 29 



;;:: 

 34 



: i 



36 

 37 



::■ 



Reel, with fork and float 



clamps, 188; guy-post clamp. 24 



764; steam gauge and connections, 7i) 



Fronl bearing point, 75; clutch post, ■ real bearing 

 3, 15." 



Separator and pipes to engines and pump. 

 Drop piece and guy-posl for rudder 



fwil houl i lamp), 2077 



Tail (without clamp) 



Rudder 



GtlJ ^t irks 



Propellers 



Extra length of midi 



w 1 bowsprit 



Canvas keel, ".0 



[ upei p. ••> d v. i. 



Fuel (al i'i ng Bighl i 

 flight). 



Sundrie 



Hying weight . 



40 

 41 

 42 

 43 

 II 

 45 

 4(1 

 17 

 48 

 40 

 .," 

 ;.i 

 52 

 53 

 54 

 55 

 56 



00 



id 

 if; 

 63 



id 



66 



70 

 71 

 72 



'1'. ital area of support (not including tail) sq. ft. 



area of support in feet, divided by total living 



weight in His 



Total area of horizontal tail sq ft. 



Total area of rudder (vertical) sq. ft. 



p wer ai brake — Horse-power by formula • 



Lift at pendulum (during one minute absolute) 



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



Minimum pressure with which wheels turn 



n of renter of pressure of wings I, to', from fronl 



ire of v. ings, t in is 



Roof angle of wings, 10" 



'lip ana i"' 



Position of wings front edge of front wing, 159. 

 I low guyed 



n e.f tail 



Angle of tail. 7' . 



of tail, 1240 grammes al center to 



ontal 



Position of rudder 



ol thrust, 1500 



Center of gravity] of whol 1484.4 



ivityj 



Center of pressure! of whole estimate. 

 



U.5 

 7.75 



Weight 



172 



274 

 297 

 5S4 

 :il5 



1 IS 

 212 

 843 



602 

 76 



3448 



323 

 106 

 020 

 371 

 12S 

 30 



175 

 1526 



13,275 



i iii end of bowsprit, 1702.! 



( 'elder of float Without .■-trail U ifid 



vane rudder, 1666.1. it lenter of 



float with wind vane rudder on, 

 11127.) 



Front end of midrod, 1013.7. 

 Front edge of F. \\\, 1585. 

 C. "f P. on P. W., 1503.7. 

 Rear edge of F. W., 1531.7. 



Line through renter of propellers, 



i; 



C. of t;.. mm. I. 

 Front edge of R. VY., 1395 

 C. "f P. on I!. \V.. 1374.5. 

 End of midrod. 1351. S. 



Front end of rudder. 1335. 

 Pa,k edge of It. W., 1342 5. 

 Center of rudder, 1279.5. 

 Hark rud of rudder, 1221. 



II. P. 



Rev, x diam. X piteh ratio x thrust 

 33OO0 



' Thnt is calculated 0] ption that the center of pressure on each wing or on pair of wings at a motion of 2000 feel pel 



•d wings 2-5 III.' way from front to rear, thai for winus of usual size the rear wintrs have 2-3 of the 

 1 oi the foul ones and that Hie tail proper bears no part of the weight; but if rear wing is smaller or larger 

 this efficiency is smaller or larger per unit of surface. 



