Hysteresis effect of oblique shock interactions in an axisymmetric steady flow
A numerical study of the interaction of two oblique shock waves has been investigated in an axisymmetric flow. The first one is produced by a conical ring with a sharp leading edge located at the exit of a supersonic nozzle. The second one is generated by a centre-body placed along the symmetry axis of the nozzle in the test chamber. The forward and backward displacement of the centre-body show experimentally three different configurations of this interaction with a double loop hysteresis between them. The numerical results have reproduced these configurations with a precise description of the flow features. But the hysteresis effect has been partially described.
KeywordsHysteresis Effect Oblique Shock Mach Stem Oblique Shock Wave Regular Reflection
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