298 



SMITHSONIAN CONTRIBUTIONS TO KNOWLEDGE 



VOL. 27 



DATA SHEET No. 2. 

 Weight of Aerodrome No. G. 



( vi ufied to by R. L. Eeed, November 21 and 28, 1896. 



Frame, including everything of metal, permanent and 

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



support of propellers, bearing points tor clutch, etc 



fin.: mi-, gears, shafts, etc 



Pump, pump shaft 



Mull covering 



! 



Smokes ! urner, 17l* 







Wing clamps, 238; drop piece for rudder, 40. 



Other things , 



Boiler, mica cover 



Separator, steam gauge, pipe to engines 



Exhaust pipe 



■ !. hi clamp), wet. 



■ ithout clamp) 















Extra length of midrod 



Wood bowsprit 



Counter 



i 'iiel I il start i ng flight I . . 

 Water (at starting i 1 



Sundries unknown . 

 i ■ tal flying wi ighi 



Total art i .1 M.i|ip n't (not including tail) sq. ft, 



Total area of support in feet, divided by total flying 



weight in lbs 



Total area of horizontal tail sq. ft, 



Total area of rudder (vertical) sq.ft. 



Horse-power at brake Horse-power by formula * 



Minimum steam pressure during 10 sees, lift 



Lift at pendulum (during one minute absolute) 



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



Minimum pressure with which wheels turn 



u of renter of pressure of wings f... 



Time of getting up full steam, 7. r > sees 



■f midrod with horizon, 2° 17' 



Curvature o! wings, I in 18, V', from front 



Root angle of wings, 10° 30' 



Tip angle of wings, 10° So' 



1 n of wings 



ruyed 



1 . r 1 1 t I 00. 



of prai Hi , of whole, 1 183 8 



r "f gravitys, 2482 ; 



11-7. 

 2520 



Weight. 



1178 



1043 

 190 

 345 

 306 



474 



276 



77 

 278 

 160 

 691 

 635 



82 



2154 



375 

 106 

 644 

 398 

 135 

 75 



X'50 

 2850 



12,120 



130 



: til 



Remarks. 



Front end of bowsprit, 17n7. 



Center of float in first trial, Nov. 

 27, 1670. 



Front end of midrod. 1613.7. 

 Front edge of 1". W., 1595 7. 



Center of fln.il in flight, Nov. 28, 

 1806, 1575.8. 



C. of P. on F. \\\, 1568.7. 

 Back edge of F. W., 1515 7. 



Line through center <>f propellers, 



1500. 



C. of G., 1M 1 (old C. of C, 

 1486.3). 



Front edge of li W., line. 

 C. "i I". on It. W., 1374. 

 End ol midrod, 1351.3. 



Front end of rudder. 1334.5. 



Back edge of li. W., 1326. 



: of rudder. 127'.'. 

 Bark end of rudder, 1220 



Reed wings, 80 cm. • 185 cm. in 

 ngle. 



Weight in shop, 1982 g. 



On day of flight they weighed 

 2154 g. because thej were damp. 



Area 54 sq. ft. 



Spread of wings, 359 cms. or 

 11' 9%". 



Weight of aerodrome in flight. 

 12,120 grs 



. _ Rev, x diam. x pitch ratio x thrust 



33000 



1,1 uiated on the assumption that the center of pressure oi b wing or on pair of wings at a motion of 2000 feet per 



I wii 1-5 Hi. waj from front to rear, that tor wings of usual size the rear wings have 2-3 of the 

 ol the front ones and that the tail proper b< u no pari of the weight; but if rear wing Is smaller or larger 

 r unit of surface. 

 ! This is undoubtedly inci i tl ■ re true, the C. G. would be |ust af the center of the separator, and this would be 



ible. Mr. Reed states that the C. G. was 2 cm. below the side frame, and if this is correct, we would have C. G. = 2486. 



