Abstract: Supercritical injection and combustion processes are prevalent in liquid rockets and hypersonic flight equipment. Under the critical state, the thermophysical and transport properties of the fluid are very sensitive to pressure and temperature, and the ideal state equation is no longer applicable. Based on the OpenFOAM open source program and by using the classical pressure implicit split operator (PISO) algorithm to couple the velocity and pressure, this paper presents a new computational fluid dynamics (CFD) solver for supercritical jet, which incorporates the Soave-Redlich-Kwong (SRK) real-fluid equation of state and takes into account the effect of the isothermal compression coefficient on the pressure equation. And the numerical validity of the model is verified against experiments of a shock tube and supercritical jet. The results show that the new model possesses good prediction accuracy and reproduces the experimental results well. The model can be further extended for applications to transcritical and supercritical spray and mixing under internal combustion engine conditions.

Key words: supercritical jet, real-fluid equation of state, computational fluid dynamics(CFD) model, pressure correction equation, shock tube