F,22 • DISSOCIATION EFFECTS 



air. The density ratio p^/ p^:, across a normal shock in free flight is plotted 

 in Fig. F,22d; this ratio was computed through simultaneous solution 

 of the continuity, momentum, and energy equations, along with the 

 equation of state in [69]. Out of this calculation also comes the tempera- 

 ture ratio (Fig. F,22e). From Fig. F,22e and Fig. F,22b is determined 

 the viscosity ratio /xVm« plotted in Fig. F,22f. The temperature ratio in 

 Fig. F,22e is of extra interest because it indicates immediately what 



1000 



a 

 _o 



+-< 

 o 



to 

 if) 

 o 



00 



10 



20 



24 



4 8 12 16 



Mach number M=o 



Fig. F,22g. Ratio of stagnation to ambient viscosity across a normal shock for air. 



temperature an insulated body would acquire, or rather, what tempera- 

 ture a body is subjected to, at very high speeds. 



The stagnation enthalpy /i° is readily computed from 



/i" = /i« + 



V 



(22-1) 



and is therefore independent of dissociation. It is noteworthy that the 

 stagnation pressure behind a shock wave is apparently also independent 

 of dissociation (see Fig. F,22g). 



(423 > 



