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基于各向异性非结构网格,实现了自适应求解技术,将其应用于超声速楔形体绕流及超声速横向喷流问题的计算研究,对各向异性网格自适应计算过程的收敛性和求解精度进行了对比分析,展示了各向异性网格自适应算法在降低问题求解规模。提高各向异性流场分辨率等方面的优势及存在的问题。超声速楔形体无粘绕流场的自适应计算,清晰地捕捉到了激波附近的流场信息,激波前后的马赫数、压力、密度。温度等物理量与理论分析解吻合很好。超声速横向喷流流场存在激波、分离涡、边界层等流场结构的相互干扰。计算研究表明,单纯基于Hes-sian度量张量的各向异性网格生成及自适应算法不能有效模拟边界层内的流动情况,是将来需要进一步开展的研究挑战。
Based on the anisotropic unstructured grid, the adaptive solution technique is implemented, which is applied to the calculation of supersonic wedged flow and supersonic transverse jet flow. The convergence and solution of the anisotropic mesh adaptive calculation process Accuracy was compared and analyzed, showing the anisotropic mesh adaptive algorithm to reduce the size of the problem solving. Improve anisotropic flow field resolution and other advantages and problems. The adaptive calculation of the supersonic wedge without viscous flow field clearly captures the flow field information near the shock wave, Mach number, pressure and density before and after the shock wave. The physical quantities such as temperature agree well with the theoretical analysis. Supersonic transverse jet flow field exists shock wave, separation vortex, boundary layer flow field structure such as mutual interference. Computational studies show that anisotropic mesh generation and adaptive algorithms based on Hes-sian metric tensor alone can not effectively simulate the flow in the boundary layer, which is a research challenge that needs to be further developed in the future.