304 



SMITHSONIAN CONTRIBUTIONS TO KNOWLEDGE 



voi>. 27 



DATA SHEET No. 8. 

 ;i of Aerodrome No. •".. Flat Wings and Penaud Rudder. 

 Certified to by Chas. M. Manly. July 19, L899. 



Parts. 



including everything of metal, permanent and 

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

 support of propellers, bearing pointe lot clutch, etc 







Pump, pump shaft 



■. pron, 115; piece behind rep iratoi 19 



Gasoline atel :iir tanks, 167, 165; air valve, lfi 



estack, 310; piece to protect midrod, B3 



: loat, 275; drop piece for rudder, 57; guy-post, is 



Reel, fort ana float, 128; steam gauge wit] pipe, 61 



Wing clamp! clamps, :'■- 



Boiler, 800; burner, tai; counter, !>.> 



ii t" midrod 



I pipes in engine ana pump 



i pipe 



Front lower bearing point. 84; clutch post, 41 



Rear bearing points, 146; extra strengtheners, 32 



Wings (without clamp) 



thout clamp), pari of rudder, 



Ruddi r 



Guy stick . i tch 56 



Propellers, 95 cm. wood 



Extra length of midrod 



w 1 t.. wsprit 



Other things 



flight) 



». Mi i (210(1 ai starting flight) • 616 in boiler. 



23 

 24 

 15 

 26 

 27 



■> 



31 Sundries unknown 



32 



33 



::i Total flying 



35 



lupport i a it m, ludins tail) sq. ft. 



a support in feet, divided by total flying 



weight in lb-- .' 



Total t horizontal tail sq.ft. 



ai ea oi ruddei (vertical) Bq, ft. 



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



Ian ,ii pendulum (during one minute absolute) 



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



Minimum pressure with which wheels turn 



Position oi center of pressui e of wings t 



Curvature of wings. 



[0 







How guyed 



n of tail 



| tin , 



1 



mtal 



■ of rudder 



two i ,-inch rubber bands ab ve ana 



i inch bands, in tandem, below 







t gravity] of whole 



, ■ ■ t \ 



Center of pressure! ,,t wholi i stimate 







Si 



Weight. 



68 



3556 



348 

 373 

 350 

 209 

 232 

 1065 

 174 

 602 

 84 

 125 

 178 



2446 



299 

 112 

 837 

 168 



78 



200 

 1400 



Remarks. 



Front ma oi bowsprit, 1683.5. 



'' ot float. 1614.5. 



Front in, I of midrod, mil. 5. 

 C. of reel and float, 1,">77."», 

 front edge of F. w., 1609.7. 

 C. of 1'. on F. \V., I.i77.7. 

 Rear edge of F. W., 1529.7. 



Line through center of propellers, 

 1500. 



('. of G.. 1498. 

 Front oils;.:- of R. W., 14Hti.7. 

 C. of P. on R. W., 1374.7. 

 laid of midrod, 1360.3. 

 Front t mi of rudder, 1343.5. 

 Back edge of It. w., 1326.7. 

 Center of rudder, 1288. 



Bat 1. i t,,I of rial. lor. I 29 ■ 



V It Distance between C. P. on 



I', w., and r. G. 7:>.7 Pis 

 tance between C. IV on R, W. 

 an.I C. G. 123.3. If Ha- mean 



t '. I', is t,, I \ er the < '. G. we 



should require an efficiency for 

 tin ir.,r winss of 04.6 %. 



II I- 



Rev, x diam. x pitch ratio y tlnn-l 

 33000 



' assumption that the center of pressure on each wing or on pair of wings at a motion of 2<mk> feet per 

 < '- ii waj Hon, front to rear, thai i , wing ol nail size the roar wings have 2-3 of the 



■1 thi ft. ait ones .til that the tail pup.! bears no part of the weight; but if rear wing is smaller or larger 

 iv is smaller or larger per unit of surface. 



