Page 219 - 48Fundamentals of Compressible Fluid Mechanics

10.2. GOVERNING EQUATION 5 181

4
5
6 :
8
7 8
7
5
6
7:
8
"
91 1
)0+
"1
"1
+9 -"1
" 9
)
The higher the entrance stagnation temperature the larger the heat amount
that can be observed by the flow. In subsonic branch the Mach number is after the

shock is 4 4 5 7 8
5 :
:
7 8 :
6
7
7 8
7
)09 "
"0
-9)
With Mach number of " +=)," 5 )19 " the maximum heat transfer requires
information from Rayleigh flow as following

6
4

5
5
6 :
8
7
7 8
5
8
7 :
"
)19 "
)19 -+
),+
" -9
+9 -"1
It also must be noticed that stagnation temperature remains constant

across shock wave.
7 8 :
6
:

5 :

+-9 1"-

: E
<
L
G
G
@

G
G
@
E
+-9 1"-
L
N
L
It is not surprising since the the shock wave are found on the Rayleigh flow. To make up a example with
E
L U&T
: U&T
G I G @ : E
<
L
:
mid range increase of tem-

G I G @
L

perature
N