Articles

Research of influence of reduced-order boundary on accuracy and solution of interior points

Expand
  • Department of Mechanics, Tianjin University, Tianjin 300072, China

Received date: 2016-02-26

  Revised date: 2016-07-22

  Online published: 2017-01-01

Supported by

Project supported by the National Key Research and Development Project of China (No. 2016YFA0401200) and the National Natural Science Foundation of China (Nos.11672205 and 11332007)

Abstract

The flow field with a high order scheme is usually calculated so as to solve complex flow problems and describe the flow structure accurately. However, there are two problems, i.e., the reduced-order boundary is inevitable and the order of the scheme at the discontinuous shock wave contained in the flow field as the supersonic flow field is low. It is questionable whether the reduced-order boundary and the low-order scheme at the shock wave have an effect on the numerical solution and accuracy of the flow field inside. In this paper, according to the actual situation of the direct numerical simulation of the flow field, two model equations with the exact solutions are solved, which are steady and unsteady, respectively, to study the question with a high order scheme at the interior of the domain and the reduced-order method at the boundary and center of the domain. Comparing with the exact solutions, it is found that the effect of reduced-order exists and cannot be ignored. In addition, the other two model equations with the exact solutions, which are often used in fluid mechanics, are also studied with the same process for the reduced-order problem.

Cite this article

Yunlong LI, Wei CAO . Research of influence of reduced-order boundary on accuracy and solution of interior points[J]. Applied Mathematics and Mechanics, 2017 , 38(1) : 111 -124 . DOI: 10.1007/s10483-017-2153-6

References

[1] Luo, J. Transition and prediction for hypersonic boundary layers. Acta Aeronautica et Astronautica Sinica, 36, 357-372(2015)
[2] Luo, J. S., Wang, X. J., and Zhou, H. Inherent mechanism of breakdown in laminar-turbulent transition. Science China Physics, Mechanics & Astronomy, 48, 228-236(2005)
[3] Dong, M. and Luo, J. S. Mechanism of transition in a hypersonic sharp cone boundary layer with zero angle of attack. Applied Mathematics and Mechanics (English Edition), 28(8), 1019-1028(2007) DOI 10.1007/s10483-007-0804-2
[4] Deng, X. G. High-order accurate dissipative weighted compact nonlinear schemes. Science in China Series A:Mathematics, 45, 356-370(2002)
[5] Zheng, M. and Zhang, H. Application of non-oscillatory and non-free-parameters dissipative finite difference scheme to the calculation of free-jet flows. Acta Aerodynamica Sinica, 7, 273-281(1989)
[6] Shu, C. W. and Osher, S. Efficient implementation of essentially non-oscillatory shock-capturing schemes. Journal of Computational Physics, 77, 439-471(1988)
[7] Shu, C. W. and Osher, S. Efficient implementation of essentially non-oscillatory shock-capturing schemes, II. Journal of Computational Physics, 77, 32-78(1989)
[8] Liu, X. D., Osher, S., and Chan, T. Weighted essentially non-oscillatory schemes. Journal of Computational Physics, 115, 200-212(1994)
[9] Jiang, G. S. and Shu, C. W. Efficient implementation of weighted ENO schemes. Journal of Computational Physics, 126, 202-228(1995)
[10] Cockburn, B. and Shu, C. W. TVB Runge-Kutta local projection discontinuous Galerkin finite element method for conservation laws II:general framework. Mathematics of Computation, 52, 411-435(1989)
[11] Poinsot, T. J. and Lele, S. K. Boundary conditions for direct simulations of compressible viscous flows. Journal of Computational Physics, 101, 104-129(1992)
[12] Tan, S. R. and Shu, C. W. A high order moving boundary treatment for compressible inviscid flows. Journal of Computational Physics, 230, 6023-6036(2011)
[13] Ferziger, J. H. and Peric, M. Computational Methods for Fluid Dynamics, Springer, New York, 39-63(2002)

Outlines

/

APS Journals | CSTAM Journals | AMS Journals | EMS Journals | ASME Journals