Numerical Simulation of Inviscid Flow in Hypersonic Regime Using a Meshless Approach and by Applying Hot Gas Effects

In this paper, a meshless approach utilizing least-squares error technique and Taylor series was used to numerically solve an inviscid hypersonic flow. Second and fourth order derivatives were used as artificial dissipation terms to stabilize the solution and prevent unwanted oscillations especially around the vicinity of shockwave. In this study, chemical reactions caused by increased temperature were assumed to be in equilibrium condition and derived graphs were used to estimate the specific heat ratio. We used an explicit four-stage Runge–Kutta method for temporal discretization of governing equations, and used local time-stepping and residual smoothing techniques to accelerate the convergence process. The results obtained from meshless approach were compared with those obtained from finite-volume method with identical point distribution, and this comparison showed that using meshless approach provides better convergence and lower computation time. Result also showed that replacing ideal gas model with real gas model and applying the hot gas effects lead to precise identification of shockwave’s location, and provides a more accurate prediction of temperature and pressure distribution behind the shockwave.