G,4 • TRANSPIRATION-COOLED BOUNDARY LAYER 



main stream, the flow through a porous wall, and the large temperature 

 variations through the boundary layer {Pr = 0.7, co = 0.7, e = 0.85, and 

 a = 0.19 were used in Eq. 4-22). A complete tabulation of these calcu- 

 lations can be found in [21]. An extension of the above wedge-type solu- 

 tion to the heat transfer in flow around cylinders of arbitrary cross section 

 for transpiration-cooled surfaces was made in [22]. 



8 6 



1- 



O 5 



o 



(U 

 CL 



^ 3 



-0.2 -0.4 -0.6 —0.8 -1.0 

 fw 

 Fig. G,4e. Effect of Mach number on surface temperature. (From [23].) 



An exact solution of the heat transfer of the compressible laminar 

 boundary on a transpiration-cooled fiat plate is made in [23]. The effect 

 of Mach number on surface temperature for different rates of coolant 

 injection are shown in Fig. G,4e. It is interesting to note that, for large 

 rates of coolant injection, the wall temperature is less dependent on Mach 

 number than for small rates of injection. 



Stability Considerations of the Laminar Boundary Layer with 

 Coolant Injection. The stability theory for the laminar boundary 



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