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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 °