Abstract
The behavior of a shock wave in a supersonic outflow at a sudden enlargement of a duct has been clarified experimentally by a schlieren optical system and static pressure measurements. A self-excited oscillation of flow with a shock wave has been observed at the downstream duct at a particular range of supply pressures in which range the outflowing jet is underexpanded at the sudden enlargement and furthermore the jet does not reattach in the downstream duct. In the oscillating flow, compression and expansion waves propagate back and forth between the sudden enlargement section and thickset of the duct, and the base-pressure in the dead-air region downstream of the sudden enlargement and the width of the outflowing jet oscillate periodically.
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