F • CONVECTIVE HEAT TRANSFER IN GASES 



bers. Indeed, more information on the laminar sublayer and transition 

 region in supersonic flow is necessary for further progress. 



The effect of heat transfer on the turbulent recovery factor can be 

 estimated by substitution of the factor T^/Te for the above factor 



(l+rX^M|) 



The same trend as with Mach number is found to appear. Thus r is 

 essentially independent of Ty,/Te also. 



0.90 



0.89 



0.88 



0.87 



0.86 



0.85 



0.84 



0.83 



0.82 



Turbulent rins ^ " x 

 Re = 107 



O MIT plate 

 A NACAcone 



XX -C^ 



Me 



Fig. F,llc. Recovery factor for a turbulent boundary layer on a flat plate 

 in air in a wind tunnel as a function of Mach number. To = 100°F. 



Reynolds analogy factor. Another item that must be known before a 

 heat transfer calculation can be made is the Reynolds analogy factor, so 

 called because it was Reynolds who concluded in 1874 that heat transfer 

 was proportional to fluid friction. The general expression for the Reynolds 



< 378 ) 



