306 



SMITHSONIAN CONTRIBUTIONS TO KNOWLEDGE 



VOL. 



DATA SHEET No. 10. 

 ,, f Aerodrome No. 5, Flat Wings and Penaud Rudder. 

 Certified to by Chas. M. Manly. July 27, L899. 



small sid 



is; netting 



luding everything of metal, permanent and 



undi . cross-roi ' tlie 



,i ,.i propelli re, - u liatts, eti I ui n 



wires and turn bucl ' ' 



•■ 



, shaft . .. u| poi i i.. pump, ...-. 

 .1 Hull oo' - »?; sides, 92; top, v<: 



. 11 ■ — 



ind air tanks, 167, 165; air valve. 



piece rear of " 



110 pii ce ' i proteel midrod, 63 



[ro| piece for rudder, 57 



>. Reel, fork an. I Boat, 12£ 



!■ Wing clamps, 202; guy posl clamps, 33 



10 Burner, 170; boiler, 75!) 



rator with tubes brazed to il 



pipe, 87; steam gauge and connect! n 

 1;; Exhaust pipe, 90; w iei '1 frame, 10 



11 Upper front bearing point and clutch post -■• 



1, !,,«..,. front bearing point, S4; lower rear bearing point 



14:;; cllltch, II 



lamp), front, 2 ■ 662; roar, 2 



i- ini (without clamp) 



1:« Rudder 



ti nt, 65; rear, iO 



21 Propellers, inn cm. round ends. 30° blade 



I. front, 171; rear, '227 



23 V ■ •; .■. .il (heai .. one) 



2 1 i ither things . . 



2. 



26 



■•7 Fuel "-• Bight i 



28 Water i 1000 at starting Bight) 







:; i Lead 



:;] Sundries unknown 



32 



38 



i rotal "hi 



35 



36 



37 



38 T ital ai ' (nol including tail) -'i ft 



39 Total .area ol Bupport in feet, divided by total flying 



weight in lbs 



10 Total area of horizontal tail sq.ft. 



41 Total area of rudder (vertical) sq. fi 



■•■'il . brake Horse-power by formula • 



13 



44 Lift at pendulum (during cue mini it ■ absolute) 



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



4t; Minimum pressure with which wheels turn 



17 Position of center of I wings t 



4S 



I ' 



50 i urvaturc of wings. 1 in 12 originally, but about 1 in 



11 now 



51 Root angle of I 



l p angle of wings. 10' 



53 Position of wings 



."I How guyed 



55 















gle of tail, 5 i 



ienl elasticity ol tail, 200 grammes at center to 

 il 



61 r iddi i 



62 







nter of grai 



. nter of gravity.... 



le estimate 



















71 



Weight 



Gramma. Pound: 



3342 

 470 

 389 



400 

 373 

 347 

 223 

 236 

 929 

 513 

 168 

 100 

 136 



271 



299 

 114 

 757 

 4H1 

 130 



226 



1500 



2.1936 



6.04 



7.64 



14,704 



Remarks. 



1 03 



i:; gra les of lead on end of 



bowsprit. 



i n d of bi wsprit. 1708. 

 C. of Heat, 1622. 

 Front en,] of midrod, lhT9. 

 Reel and float, 1601.5. 

 Front edge of F. W., 1609.7. 

 C. of P. on F. \V., 1577. 7. 



Hear edge of F. «.. 1529.7. 



Line through center of propellers, 

 1500. 



c, of G., Mi's. 



Front edge of it. W.. l|o|.7. 



C. of P. on II. W., 1372.7. 

 End of midrod, 1350.3. 

 Front end of rudder, 1333.5. 



Back edge of It. W., 1324.7. 

 Centre "f rudder. 1270.5. 

 Rear end of rudder, 1222. 



Distance between C. 1". on F. W. 



o , 1.7. Distance 



between C. 1'. on u. w., and C. 



i, 12 i.S, H the mean C. 1'. 



. |, ' over the i '. 0, we 



.1 Id require an effii iem J ol 



03.0 for the rear wings. 



Rev. x diam. x pitch ratio x thrust 



* H P = 



"■ ' ' 33000 



f This is calculated on the assumption that the center of pri i ch wing or on pair of wings it a motion of 2000 feel pel 



j the way from front t" rear, that for wings of usual size the rear wings have 2-3 

 ,,f tie front ones and thai the tail proper bears no part of the weight: but if rear wing is smaller or larger 

 this c: ger per unit of sun., 



