F • CONVECTIVE HEAT TRANSFER IN GASES 



0.83 

 0.82 



0.81 



M- 



Oi 0.80 



_o 

 o 



C 0.79 



o 



12 0.78 

 o 



1 0-77 

 0.76 



4 6 8 



Mach number Me 



10 



12 



Fig. F,5u. Reynolds analogy factor for a laminar boundary layer on an 

 insulated flat plate in a wind tunnel at various supply temperatures. 



0.83 



'^ 0.82 br 



o 



? 0.81 



H- 



g^ 0.80 



O 



c 

 o 



(/) 



o 



c 



>s 



0.79 



7^ 0.78 



0.77 



0.76 



500 1000 1500 



Supply temperature, °F 



2000 



Fig. F,5v. Reynolds analogy factor for a laminar boundary layer on an 

 insulated flat plate in a heated wind tunnel for various Mach numbers. 



Prt, for a supply temperature of 100°F. Fig. F,5t and F,5v are cross plots 

 in Fig. F,5s and F,5u. All curves include variable specific heat from supply 

 chamber to test section. 



F,6. Cone Solution. Hantzsche and Wendt [6] have shown that the 

 equations for a thin laminar boundary layer on a circular cone at zero 

 angle of attack in a supersonic stream with attached shock wave can be 



< 362 ) 



