论文部分内容阅读
本文采用实质上为二阶精度的无波动、无自由参数的耗散差分格式(NND格式)求解了非定常的二维和三维完全N-S方程,对类似于航天飞机头部外形的超声速粘性气体绕流流场进行了模拟。在计算中,使用了代数网格生成技术,对脱体激波采用了装配法。作为验证算例的二维圆柱绕流计算结果同文献[4]的数据进行了比较。二维凹陷外形绕流的计算结果同无粘流结果进行了对比,由于粘性流动出现了分离,二者的壁面压力是有差异的。最后,对三维外形的绕流也进行了模拟,计算结果提供了流场的细节。
In this paper, unsteady two-dimensional and three-dimensional complete Navier-Stokes equations are solved using the undivided, free-form dissipative difference scheme (NND format) which is essentially second-order precision. The supersonic viscous gases similar to the shuttle’s shape The flow field was simulated. In the calculation, algebraic grid generation technology was used, and the assembly method was adopted for the off-body shock wave. The calculation results of the two-dimensional circular cylinder flow as a validated example are compared with the data in [4]. Computation results of flow around two-dimensional dimples are compared with the results of no-viscous flow. Because of the separation of viscous flow, the pressures on the two walls are different. Finally, the three-dimensional shape of the flow around the flow were also simulated, the calculation results provide the details of the flow field.