F,18 ■ EFFECT OF TUNNEL TURBULENCE 



of Fig. F,17c shows the effect of Mach number on transition for the zero 

 heat transfer case. It is thus generally seen from the figure that transition 

 seems to follow the same trends predicted for the stability of the laminar 

 boundary layer, not only with cooling, but also with increase in Mach 

 number for an insulated surface. 



F,18. Effect of Supply Tunnel Turbulence. The data in Fig. 

 F,17c are for a smooth model (10-micro-inches) in a wind tunnel with 



10 



X 





0.5 



0.9 



1.3 



1.7 



Tw/Te 



Fig. F,18a. Effect of supply turbulence on transition 

 with, cooling. Me = 1.90; 10° smooth cone. 



( 399 > 



