F,5 • NUMERICAL RESULTS 



0.82 



0.81 



0.80 



0.79 



0.78 



0.77 



12 3 4 5 6 



Enthalpy ratio h^ (0) 



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

 flat plate in free flight for various Mach numbers. T^ = 400°R. 



0.5 



0.4 



loj 0.3 



Ul 



0.2 



0.1 



4 6 8 10 12 14 



Mach number Me 



16 



Fig. F,.5p. Local heat transfer coefficients for a laminar boundary layer on an 

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



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