F,20 • AERODYNAMIC HEATING OF HIGH SPEED VEHICLES 



200 



160 



I 

 O 



Xl20 



CD 



-a 



< 



2 4 6 8 10 12 



Velocity, (ft/sec) X lO'^ 



Fig. F,20e. Flat plate flight temperature at point 5 ft 

 from leading edge. Laminar boundary layer. 



14 



16 



200 



O 



X 



0) 



IS 



< 



160 



120 



2 4 6 8 10 12 



Velocity, (ft/sec) X lO'^ 



Fig. F,20f. Flat plate flight temperature at point 5 ft 

 from leading edge. Turbulent boundary layer. 



Eq. 20-1 presupposes relatively slow change in motion of the vehicle, 

 depending of course on how thick the skin really is. Apparently the 

 method is satisfactory for the boosting of missiles (such as the V-2) 

 when the skin thickness is of the order -^ inch and the acceleration is 

 about 5 g's. For highly transient conditions, such as with ballistic dive-ins, 

 it would be necessary to allow for the variation of temperature across the 



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