F,7 • STAGNATION POINT SOLUTION 



Eq. 7-8 is plotted in Fig. F,7a. Also plotted in the figure are experi- 

 mental values of /3 at the stagnation point of a hemispherical nose on the 

 end of a cylinder in a wind tunnel. The values were obtained by Korobkin 

 [11] from surface-pressure measurements. The theory seems to follow the 

 data quite well over the whole supersonic range. 



Fig. F,7a. Local velocity gradient at the stagnation 

 point of a hemisphere-cylinder combination. 



1.1 

 1.0 



0.9 



1^0.8 



Ul 



0.7 

 0.6 

 0.5 



0.4 







0.5 



1.0 



x/D 



Fig. F,7b. Local heat transfer data for a 

 hemispherical nose at Mach number 1.97. 



Eq. 7-lb, 7-2b, and 7-3b can also be used to yield approximate results 

 when the speed is so great that the air dissociates behind the shock 

 and in the boundary layer. However, this topic will be discussed later in 

 Art. 22. 



When the flow over the nose of a blunt body is completely laminar, 



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