Solid rocket engine active injection high modulus test suction mass flow rate method

The invention relates to the field of solid rocket engines, in particular to a solid rocket engine active injection high modulus test suction mass flow rate method. The method comprises the following steps: establishing a two-dimensional infinite long slit suction mass flow rate calculation model; obtaining a front edge sweepback suction mass flow rate through a circular hole suction mass flow rate model; deducing a critical condition of suction choking, and determining a choking pressure ratio according to an isentropic relationship when the wavefront Mach number and the waverear Mach number are determined; the suction mass flow rate model is verified, the effectiveness of the model is verified through FLUENT numerical simulation, the subsonic velocity front edge is used as the supersonic velocity front edge for calculation, the area in the model is taken as the area of a round hole, and comparison verification is conducted through the model and a numerical simulation result. The device is not only suitable