The Compressible flow structure behind the exit of a two-dimensional supersonic micro-nozzle

2차원 소형 초음속 노즐 하류의 압축성 유동 구조 해석

This paper presents the computational results for the two-dimensional compressible non-reacted flow in a converging-diverging micro thrust nozzle of which the ratio of exit to throat width (0.541 in.) is 1.8. The RNG model is applied to calculate the turbulence by loading the standard coefficients. The results agreed very well with the experiments in the view of the shock structure and the pressure distribution at the various pressure ratios between the stagnation and the environmental states. The plume structures are also discussed on the view of the shock-cell structure.