Mesh convergence error estimations for compressible inviscid fluid flow over airfoil cascades using multiblock structured mesh
This work deals with estimations of errors, which are a consequence of a finite spatial discretisation that appears while solving differential equation numerically. More precisely, it deals with the estimation of errors that occur while computing compressible inviscid fluid flow over 2D airfoil casc...
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| Format: | Article |
| Language: | English |
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University of West Bohemia
2023-06-01
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| Series: | Applied and Computational Mechanics |
| Subjects: | |
| Online Access: | https://www.kme.zcu.cz/acm/acm/article/view/827/635 |
| _version_ | 1797793635634249728 |
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| author | Tater A. Holman J. |
| author_facet | Tater A. Holman J. |
| author_sort | Tater A. |
| collection | DOAJ |
| description | This work deals with estimations of errors, which are a consequence of a finite spatial discretisation that appears while solving differential equation numerically. More precisely, it deals with the estimation of errors that occur while computing compressible inviscid fluid flow over 2D airfoil cascades. This flow is described by the 2D Euler equations that are solved by the finite volume method in their conservative form. Numerical computations are performed on structured meshes consisting of four blocks, so the number of cells in the mesh can be easily adjusted. In this work, two estimation methods are used. Firstly, the grid convergence index is used to estimate the amount of cells needed to obtain certain accuracy of the solution. Secondly, the Richardson extrapolation is used to approximate the exact solution from a series of solutions obtained with meshes of different sizes. This analysis is performed on a well-known compressor cascade, which is composed of NACA 65 series airfoils. The obtained results should lead to a reasonable choice of the number of elements in a computational mesh based on the required accuracy of the solution and therefore also to computational time reduction while performing airfoil cascade computations. The results indicate that even for very precision demanding applications, 100 000 is a sufficient number of cells in a mesh. |
| first_indexed | 2024-03-13T02:51:11Z |
| format | Article |
| id | doaj.art-1c34192199ba4337b29270587a54d514 |
| institution | Directory Open Access Journal |
| issn | 1802-680X 2336-1182 |
| language | English |
| last_indexed | 2024-03-13T02:51:11Z |
| publishDate | 2023-06-01 |
| publisher | University of West Bohemia |
| record_format | Article |
| series | Applied and Computational Mechanics |
| spelling | doaj.art-1c34192199ba4337b29270587a54d5142023-06-28T11:29:02ZengUniversity of West BohemiaApplied and Computational Mechanics1802-680X2336-11822023-06-01171718410.24132/acm.2023.827Mesh convergence error estimations for compressible inviscid fluid flow over airfoil cascades using multiblock structured meshTater A.0Holman J.1Czech Technical University in Prague, Department of Technical Mathematics, Prague, Czech RepublicCzech Technical University in Prague, Department of Technical Mathematics, Prague, Czech RepublicThis work deals with estimations of errors, which are a consequence of a finite spatial discretisation that appears while solving differential equation numerically. More precisely, it deals with the estimation of errors that occur while computing compressible inviscid fluid flow over 2D airfoil cascades. This flow is described by the 2D Euler equations that are solved by the finite volume method in their conservative form. Numerical computations are performed on structured meshes consisting of four blocks, so the number of cells in the mesh can be easily adjusted. In this work, two estimation methods are used. Firstly, the grid convergence index is used to estimate the amount of cells needed to obtain certain accuracy of the solution. Secondly, the Richardson extrapolation is used to approximate the exact solution from a series of solutions obtained with meshes of different sizes. This analysis is performed on a well-known compressor cascade, which is composed of NACA 65 series airfoils. The obtained results should lead to a reasonable choice of the number of elements in a computational mesh based on the required accuracy of the solution and therefore also to computational time reduction while performing airfoil cascade computations. The results indicate that even for very precision demanding applications, 100 000 is a sufficient number of cells in a mesh.https://www.kme.zcu.cz/acm/acm/article/view/827/635airfoil cascadegrid convergence index2d inviscid fluid flownaca 65 seriesstructured mesh |
| spellingShingle | Tater A. Holman J. Mesh convergence error estimations for compressible inviscid fluid flow over airfoil cascades using multiblock structured mesh Applied and Computational Mechanics airfoil cascade grid convergence index 2d inviscid fluid flow naca 65 series structured mesh |
| title | Mesh convergence error estimations for compressible inviscid fluid flow over airfoil cascades using multiblock structured mesh |
| title_full | Mesh convergence error estimations for compressible inviscid fluid flow over airfoil cascades using multiblock structured mesh |
| title_fullStr | Mesh convergence error estimations for compressible inviscid fluid flow over airfoil cascades using multiblock structured mesh |
| title_full_unstemmed | Mesh convergence error estimations for compressible inviscid fluid flow over airfoil cascades using multiblock structured mesh |
| title_short | Mesh convergence error estimations for compressible inviscid fluid flow over airfoil cascades using multiblock structured mesh |
| title_sort | mesh convergence error estimations for compressible inviscid fluid flow over airfoil cascades using multiblock structured mesh |
| topic | airfoil cascade grid convergence index 2d inviscid fluid flow naca 65 series structured mesh |
| url | https://www.kme.zcu.cz/acm/acm/article/view/827/635 |
| work_keys_str_mv | AT tatera meshconvergenceerrorestimationsforcompressibleinviscidfluidflowoverairfoilcascadesusingmultiblockstructuredmesh AT holmanj meshconvergenceerrorestimationsforcompressibleinviscidfluidflowoverairfoilcascadesusingmultiblockstructuredmesh |