In order to explore the aerodynamic performance at off-design points

taking an supersonic first stage of three-stage highly-loaded low-reaction aspirated compressor as research objection

the variation of parameters and inner flow filed for an supersonic first stage operating at various speeds

aspiration mass flow rates

and near stall point were investigated by numerical simulations. As a result

the aspiration schemes of the aspirated compressor designed with the low-reaction concept can still meet the design demands at various speeds; the reduction of aspiration mass flow rate will not only decrease the stage aerodynamic performance

but also affect the matching with the next stage; the working range of aspirated compressor can be further broadened by adding additional aspirated slot/holes before the endwall aspiration slot.