349 



TABLE 345.— COMPRESSIBLE FLOW TABLES FOR AIR (concluded) 



2 



El - (Mi\ (Ji\ 

 Pi \M 2 ) \ pj 



where 



Vj_ _ pj_ 

 Vi ~ P2 



a = speed of sound in air. 



A =■ cross-sectional area of the stream tube. 



Act = cross-sectional area of the stream tube for Mi = 1.0. 



F c = compressibility factor, increase in pressure above the static pressure set up in 

 a tube whose open end is pointed into the relative wind divided by the 

 dynamic pressure. 



M = Mach number 



o 



<p = Mach angle, degrees. 



p = absolute pressure. 



7\= temperature, °F absolute. 



V — airspeed, feet per second, computed for r = 520°F absolute and a = 

 1117.372 feet per second. 



7 = ratio of specific heats, taken as 1.400. 



v= expansion angle required to change Mach number from 1.0 to Mi, degrees, 

 p = mass density of air. 

 Subscripts : 



= stagnation conditions before shock. 



1 = air stream conditions before shock. 



2 = air stream conditions behind shock. 



3 = stagnation conditions behind shock. 



ISENTROPIC 



(m cr = i.o) 

 subsonic stream-tube flow 



isentropic 

 diffusion 



H H 



ISENTROPIC EXPANSION . | 



+} ^\ 



I NORMAL|V> = 

 1 S HOCK ' _^ 



(M CR = I.O) 

 SUBSONIC STREAM -TUBE FLOW 



TWO-DIMENSIONAL 



FLOW AROUND A CORNER 



Fig. 13. — Illustrating three types of flow, 

 SMITHSONIAN PHYSICAL TABLES 



