Compressible Flow Tables

Part 4: Oblique Shock Waves (Isentropic Flow, Gamma=7/5)

Notation :

M1 = Upstream Flow Mach number
M2 = Downstream Flow Mach Number
d = (Delta) Flow deflection angle
Th = (Theta) Wave Angle
P2/P1 = Ratio of static pressures across wave

 ------------------------------------------
|   M1      d   |      Weak Solution       |
|               |   Th	 |    M2  |  P2/P1 | 
|------------------------------------------|
| 1.05 | 0.0    | 72.25  | 1.050  | 1.000  |
|------|--------|--------|--------|--------|
| 1.10 | 0.0    | 65.38  | 1.100  | 1.000  |
| 1.10 | 1.0    | 69.81  | 1.039  | 1.077  |
|------|--------|--------|--------|--------|
| 1.15 | 0.0    | 60.41  | 1.150  | 1.000  |
| 1.15 | 1.0    | 63.16  | 1.102  | 1.062  |
| 1.15 | 2.0    | 67.01  | 1.043  | 1.141  |
|------|--------|--------|--------|--------|
| 1.20 | 0.0    | 56.44  | 1.200  | 1.000  |
| 1.20 | 1.0    | 58.55  | 1.158  | 1.056  |
| 1.20 | 2.0    | 61.05  | 1.111  | 1.120  |
| 1.20 | 3.0    | 64.34  | 1.056  | 1.198  |
|------|--------|--------|--------|--------|
| 1.25 | 0.0    | 53.13  | 1.25   | 1.000  |
| 1.25 | 1.0    | 54.88  | 1.211  | 1.053  |
| 1.25 | 2.0    | 56.85  | 1.170  | 1.111  |
| 1.25 | 3.0    | 59.13  | 1.124  | 1.176  |
| 1.25 | 4.0    | 61.99  | 1.072  | 1.254  |
| 1.25 | 5.0    | 66.59  | 0.999  | 1.366  |
|------|--------|--------|--------|--------|
| 1.30 | 0.0    | 50.29  | 1.300  | 1.000  |
| 1.30 | 1.0    | 51.81  | 1.263  | 1.051  |
| 1.30 | 2.0    | 53.48  | 1.224  | 1.107  |
| 1.30 | 3.0    | 55.32  | 1.184  | 1.167  |
| 1.30 | 4.0    | 57.42  | 1.140  | 1.233  |
| 1.30 | 5.0    | 59.96  | 1.090  | 1.311  |
| 1.30 | 6.0    | 63.46  | 1.027  | 1.411  |
|------|--------|--------|--------|--------|
| 1.35 | 0.0    | 47.80  | 1.350  | 1.000  |
| 1.35 | 1.0    | 49.17  | 1.314  | 1.051  |
| 1.35 | 2.0    | 50.64  | 1.277  | 1.104  |
| 1.35 | 3.0    | 52.22  | 1.239  | 1.162  |
| 1.35 | 4.0    | 53.97  | 1.199  | 1.224  |
| 1.35 | 5.0    | 55.93  | 1.157  | 1.292  |
| 1.35 | 6.0    | 58.23  | 1.109  | 1.370  |
| 1.35 | 7.0    | 61.18  | 1.052  | 1.466  |
| 1.35 | 8.0    | 66.92  | 0.954  | 1.633  |
|------|--------|--------|--------|--------|
| 1.40 | 0.0    | 45.59  | 1.400  | 1.000  |
| 1.40 | 1.0    | 46.84  | 1.365  | 1.050  |
| 1.40 | 2.0    | 48.17  | 1.330  | 1.103  |
| 1.40 | 3.0    | 49.59  | 1.293  | 1.159  |
| 1.40 | 4.0    | 51.12  | 1.255  | 1.219  |
| 1.40 | 5.0    | 52.78  | 1.216  | 1.283  |
| 1.40 | 6.0    | 54.63  | 1.174  | 1.354  |
| 1.40 | 7.0    | 56.76  | 1.128  | 1.433  |
| 1.40 | 8.0    | 59.37  | 1.074  | 1.526  |
| 1.40 | 9.0    | 63.19  | 1.003  | 1.655  |
|------|--------|--------|--------|--------|
| 2.20 | 0.0    | 27.04  | 2.200  | 1.000  |
| 2.20 | 2.0    | 28.59  | 2.124  | 1.127  |
| 2.20 | 4.0    | 30.24  | 2.049  | 1.265  |
| 2.20 | 6.0    | 31.98  | 1.974  | 1.417  |
| 2.20 | 8.0    | 33.83  | 1.899  | 1.583  |
| 2.20 | 10.0   | 35.79  | 1.823  | 1.764  |
| 2.20 | 12.0   | 37.87  | 1.745  | 1.961  |
| 2.20 | 14.0   | 40.10  | 1.666  | 2.176  |
| 2.20 | 16.0   | 42.49  | 1.583  | 2.410  |
| 2.20 | 18.0   | 45.09  | 1.496  | 2.666  |
| 2.20 | 20.0   | 47.98  | 1.404  | 2.949  |
| 2.20 | 22.0   | 51.28  | 1.301  | 3.270  |
| 2.20 | 24.0   | 55.36  | 1.181  | 3.655  |
| 2.20 | 26.0   | 62.70  | 0.980  | 4.292  |
 ------------------------------------------

Reference : Compressible Fluid Dynamics, Philip Thompson, McGraw-Hill, 1972

© 1997,1998
Aerospace,Mechanical and Mechatronic Engineering, University of Sydney.