Abstract
A numerical code aiming to simulate two-dimentional compressible flow, modeled by Euler equations with immersed boundaries, was submitted on a verification test using the Method of Manufactured Solutions. The code was developed to study computational aeroelasticity flutter analysis by means of forced oscillations on the NACA 0012 airfoil section modeled by the Immersed Boundary Method. Finite Difference scheme using Steger-Warming method of second order of accuracy to the spatial discretization and a Runge-Kutta method of fourth order of accuracy to the time discretization were used. It was created a manufactured solution that mimics a compressible flow with presence of shock waves. The numerical code was submitted by a Mesh Refinement Test and a systematic analysis of actual order of accuracy was performed. The results indicated that the code was free of programming errors and the Method of Manufactured Solutions was a good tool for debugging the code.
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