"I — I — I — r 



O Rj = 2.5 (10)^ 

 A R^ = 5 (10)^ 



C, = 0.0525 (2.94 + a deg) 



-8-6-4 



8 10 



-20246 

 ANGLE OF ATTACK a (deg) 



Figure 18 - Lift Coefficient as a Function of Angle 

 of Attack — Parent Foil 





' 



1 1 1 1 1 1 1 1 1 1 



1 ' 1 'o 



0.05 



— 



O R^ = 2.5 (10)6 



- 





- 



^ Re=5(10)6 

 CURVE FIT (R^ = 5 (10)^) 



J/ - 



0.04 



- 





/ - 



Q 

 U 



1- 



z 



lU 



O 0.03 



- 





/ - 



u. 

 u. 







y 



O 



u 



- 





"^ 



g 0.02 



-\ 





— 





-O^ 





- 



0.01 



— 





— 





1 



1 . 1 . 1 . 1 . 1 . 



1 . i . 



-0.2 



-0.1 



0.1 



0.2 0.3 

 C. 



0.4 



0.5 



0.6 



Figure 19 - Drag Coefficient as a Function of Lift Coefficient — Parent Foil 



28 



