353 



TABLE 346A.— FORCES ON AIRFOILS AT ANGLES TO THE WIND 

 (FIGS. 14, 15) (concluded) 



NACA 64.-0I2 AIRFOIL 



NACA 64- 02 1 AIRFOIL 



4 



•032 



.024 



.016 



008 



.20 



CP 



.40 



4 .4 .8 



LIFT COEFFICIENT C, 



1.6 



Fig. 14. — Force coefficients for two symmetrical airfoils of infinite aspect ratio plotted 

 against angle of attack, a, for Reynolds number 6 X 10°. 



.6 .06 

 .4 .04 



.2 .4 .6 .8 



MACH NUMBER, M 



Fig. 15.— The force coefficients, Cl, Cd, and CP, plotted against Mach number for a 

 9-percent thick airfoil at an angle of attack of 2° and Reynolds number from .35 X 10° 

 to .75 X 10 8 . 



SMITHSONIAN PHYSICAL TABLES 



