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Table 1 Comparison of theoretical and present numerical results obtained from the supersonic oblique shock configuration

From: A sharp-interface immersed boundary method for simulating high-speed compressible inviscid flows

Case

Flow variables

Exact

Present

Ma1 = 3.0

Ma2

2.255

2.255

p2/p1

2.822

2.821

T2/T1

1.388

1.388

Shock-angle

32.24 °

32.21 °

Ma1 = 5.0

Ma2

3.504

3.504

p2/p1

4.781

4.781

T2/T1

1.736

1.736

Shock-angle

24.32 °

24.31 °