Investigation of the pseudo-shock wave in a two-dimensional supersonic inlet

摘要: AbstractThis paper describes experimental and numerical investigations into the multiple shock waves/turbulent boundary layer interaction in a supersonic inlet. The test model has rectangular shape with an asymmetric subsonic diffuser of 5°. Experiments were conducted to obtain visualization images static pressure data by using wind tunnel. Numerical simulation was performed solving RANS equations Menter’s SST turbulent model. inflow condition free-stream Mach number 2.5 unit Reynolds 7.6 × 10 7 /m. results showed good agreement results. Based on this agreement, flow characteristics which are often very difficult experimentally alone analyzed aid simulation. structures, velocity distributions, total loss pseudo-shock wave inlet presented detail from pressures.Graphical Abstract[IMAGE]