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238 Chapter 12 Compressible Flow Analysis

Values in these equations are average between the left and right
cell values,
 H   H
 =  L  ; H = L L R R
R
   R
L
 u   u  v   v
u = L L R R ; v = L L R R
   R    R
L
L
where the subscripts L and R refer to the left and right cells,
respectively.

12.3 Academic Example

12.3.1 Mach 3 Flow over Inclined Plane

y

Shock wave . 454
M  3 0 . 1

  Inviscid . 546
Symmetry   20 wall
x
5 . 0 . 1 5

  1.4 ; R  287 msec  K ; T  300 K
2
2
M  3 ; a  347.19 msec ; u  1041.57 msec
  1.18 kg m ; p  101598 Nm
2
3
c  1004.5 msec  K
2
2
p
A Mach 3 inviscid flow over an inclined plane is
probably one of the simplest examples for understanding the
compressible flow behavior. The problem statement is shown in