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用单元中心有限体积法在物理空间曲线网格离散积分形式N S方程,用坐标变换计算粘性通量项中的各偏导数值,用Runge Kutta三步显式格式进行时间推进求解。采用了人工粘性、当地时间步长及隐式残值光顺。计算了旋成体大迎角涡流和带底部喷流的绕流场。计算中发现,各向异性隐式残值光顺较之各向同性隐式残值光顺能更快地加速迭代过程的收敛。计算的物面压力分布与实验基本符合,计算的旋成体大迎角涡流图谱合理。计算结果说明底部喷流对旋成体绕流及空气动力载荷有显著影响。
The finite element method was used to discretize the integral equation N S equation in the curve space of the physical space. The partial derivatives in the viscous flux term were calculated by coordinate transformation. The Runge Kutta three-step explicit format was used to solve the time-delay problem. Artificial viscosity, local time step and implicit salvage value smooth. The turbulence flow at the high-angle of attack and the jet flow at the bottom are calculated. It is found in the calculation that the anisotropic implicit salvage value smoothes the convergence of the iterative process more quickly than the isotropic salient salvage value. The calculated object surface pressure distribution is in good agreement with the experiment, and the computed swirl spectrum at high angle of attack is reasonable. The calculation results show that the bottom jet has a significant influence on the flow around the body and the aerodynamic load.