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Abstract




This paper compares the results of Computational Fluid Dynamic (CFD) and analytical method when applying to the case of supersonic flow over main wing of S-125 Neva/Pechora surface-to-air missle. The theory of two-dimensional, steady, inviscid supersonic flow over oblique surface, equations of relations between Mach number, pressure, temperature of flow in front and behind of shock wave, details of MATLAB algorithm and Spalart-Allmaras turbulent model will be displayed in this paper. Meshing process had been done by Meshing module and numerical simulation process had been done by Fluent module of ANSYS software. The results of two methods were presented in graphs of Mach number, pressure, temperature distributions along the chord line of wing. The reasons of differences between two results will be presented at the end of this paper.






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Article Details

Issue: Vol 20 No K1 (2017)
Page No.: 84-90
Published: Mar 31, 2017
Section: Engineering and Technology - Research article
DOI: https://doi.org/10.32508/stdj.v20iK1.419

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Creative Commons License

Copyright: The Authors. This is an open access article distributed under the terms of the Creative Commons Attribution License CC-BY 4.0., which permits unrestricted use, distribution, and reproduction in any medium, provided the original author and source are credited.

 How to Cite
Nam Tran, H., Anh Vu, N., & Nam Le, T. P. (2017). Comparing the results of analytical method and numerical simulation method for supersonic flow over main wing of S-125 Neva/Pechora missle. VNUHCM Journal of Science and Technology Development, 20(K1), 84-90. https://doi.org/https://doi.org/10.32508/stdj.v20iK1.419

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