Pressure recovery measurement in a supersonic ejector using a centerline pressure probe

The objective of the present work is to experimentally study the pressure recovery process that occurs in supersonic ejectors. Pressure measurements are achieved using a specific sliding measuring system for the centerline static pressure. The axial displacement of this weakly intrusive system allows the measurement of axial distribution of static pressure inside the mixing zone where the shock train is formed. Experiments are realized both in mixed flow and fully supersonic regimes. They are carried out in a supersonic air-to-air ejector but may be applicable to other gases. The obtained results allow the detection between the different flow regimes and the understanding of the complex pressure recovery process which takes place in supersonic ejectors.