78 



SMITHSONIAN MISCELLANEOUS COLLECTIONS 



VOL. 62 



Curtiss has been given greater wing area in order to reduce the 

 loading. It should be stated that the comparison is not quite fair, 

 since the total weight of the Clark aeroplane was taken as 1,600 

 pounds which includes only half the full 5.6 hours' gasolene supply. 

 However, the advantage of light wing loading is more clearly brought 

 out by the marked difference in weight per square foot wing area. 



The following table summarizes all the information available and 

 may be used to make further comparisons if desired: 



Clark Tractor - 



Wing area 



Mean span 



Mean chord 



Mean gap 



Area, fixed tail... . 

 Area, elevators... . 



Area, rudder 



Length, body 



Weight, lbs 



Rise of wing 



Lbs. per sq. ft 



Angle of incidence 

 V, miles, hour. . . . 



U, ft. -seconds 



m 



Ka, feet 



Kg, feet 



Yv 



U 



Nv 



Yv 



Lv 



Nv 



Yr 



Lr 



Nr 



A; 



B2 



C2 



D', 



£2 



Kouth's discr 



Spiral Motion 

 Damp 50% in, sec. 

 Double in, sec 



Rolling 



Damp 50% in, sec. 

 "Dutch Roll" 



Period, sec. 



Damp 50% in, sec. 

 Double in, sec 



464.0 

 40.2 

 5-77 

 6.37 

 16. 1 

 16.0 

 9-35 

 24-5 

 1600 

 i°63 

 3-55 

 0° 



76.9 



■112. 5 



50.0 i 



5.2 i 



6.975 



.204 



3.06 : 



— .449 

 o 



—631.0 

 o 

 o 



+ 770 



— 39.4 

 I3I0.0 



31800.0 

 32700.0 

 41780.0 



2770.0 

 37x10^'' 



! 



10.4 I 



Curtiss Tractor^ 



Bleriot 

 Monoplane* 



6?o 



44-6 



i— 65.3 



-f 



+ 3.44 



— -351 

 o 



—319.0 

 + 33.5 

 o 



+132.5 



— 26.0 

 I3I0.0 



16350.0 

 5910.0 

 5490.0 

 1386.0 

 12X10'" 



2.7 



• 03 



5.9 



1-4 



.06 



10.7 

 1.3 



'+ 



\+ 



o 



24 



57 



o 



+ 160 



-38 



1310 



12090 



1630 



3490 



—335 



4X10' 



106 



91 



53 



384.0 



36.0 



5.3 



5.3 



23.0 



19.0 



7.8 



26.0 



1800 ..... 



0° ..... 



5^2 ••■V 



i.o 15.5 



78.9 43-6 



—115. 5 — 63.8 



56.0 



6.06 



3.4 I I 



. 248 — . 09 



+ .8441+ .2.7 \ 



— .894— .45; 

 o ! 



—314.0 I— 78.0 



o !+ 37.7 



o I o 



+ 55.2 i+IOI.O 



— 27.0 — 30.4 

 2590.0 2590.0 



23800.0 6860.0 



18000.0 I 209.0 



34600.0 5590.0 



—855.0 ' II75.0 



9X10'' —7X10' 



7.2' 28.0' 



I 



. 076 . 08 



12.0 



5-95 



5.24 

 1.77 



3.3 



.26 



5.7 

 7.66' 



* Unstable. 



* Tested at Mass. Institute of Technology, Boston. 

 ' Tested at Teddington, England. 



244.0 



1800 

 i°8 



6?o 

 65.0 



— 95.4 

 56.0 



5.0 

 6.0 



— .108 

 + .70 



— .44 

 o 



— 167.0 

 + 24.0 





 + 54-0 



— 31.0 

 900.0 



6780.0 

 5580.0 

 6640.0 



— 68.0 

 21.5X10'" 



68.0' 



6.5 

 1.65 



