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本文对轴对称超音速羽流流场进行了数值计算和实验研究。数值计算方法是空间步进的分离系数矩阵差分法,并用粘性和无粘分裂法处理粘性问题。同时对同轴超音速喷流进行了流场观察和测量,所得纹影照片清晰地显示了尾喷流场的详细结构。计算结果在近场与文献[1]一致,在远场与本文的实验结果基本一致。计算实践表明,与中心差分格式相比,分离系数矩阵方法的稳定性好,精度高,捕捉的激波耗散小,且无数值振荡。
In this paper, the axial symmetric supersonic plume flow field is numerically calculated and experimentally studied. The numerical calculation method is spatial step separation coefficient matrix difference method, and sticky and non-stick splitting method is used to deal with the viscosity problem. At the same time, the flow field of the coaxial supersonic jet flow was observed and measured. The resulting smear image clearly shows the detailed structure of the jet flow field. The calculated results are consistent with the literature [1] in the near field and basically the same with the experimental results in the far field. Computational practice shows that compared with the central difference scheme, the separation coefficient matrix method has the advantages of good stability, high precision, small shock wave capture, and no numerical oscillation.