Comparing the results of analytical method and numerical simulation method for supersonic flow over main wing of S-125 Neva/Pechora missle

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.