Abstract
The goal of this paper is to implement an accurate and robust solver for compressible Navier-Stokes equations coupled with the Spalart–Allmaras model, which possesses the capability of shock-capturing and predication of boundary layer and separated flow. In a given stencil width, a WENO-Z scheme equipped with Roe flux difference split method is used to calculate the inviscid flux, and central differencing scheme for the viscous terms are employed. The explicit Runge-Kutta is adopted for the temporal discretization. The simulation results of selected cases are given to verify the validation of the solver.
Highlights
Computational fluid dynamics (CFD) acts as an indispensable tool for widely industrial applications, such as aerospace, ocean engineering, weather environment, vehicle design and so on [1]
Laminar boundary layer Primarily, a simple case of the laminar flow over an adiabatic flat plate at Mach number Ma∞=0.2 and Reynolds number Re=1.3×106 based on the plate length [11], is employed to examine the Navier-Stokes equations solver without turbulence model
In the current work, a high-order solver is developed for compressible Navier-Stokes equations embedded the SA model, which can capture shock wave and describe turbulence flow
Summary
Computational fluid dynamics (CFD) acts as an indispensable tool for widely industrial applications, such as aerospace, ocean engineering, weather environment, vehicle design and so on [1]. Direct numerical simulation (DNS), large eddy simulation (LES) and Reynolds averaged Navier-Stokes (RANS) simulation, are the dominant methods for the numerical solution of the turbulence flow [2]. With the consideration of computation requirement and efficiency, RANS techniques, which rely completely on modeling assumptions to represent turbulent characteristics, are the most common and popular method for the complex and large-scaled industrial problems. Most of the engineering applications is 2nd-order numerical accuracy solver, which is inadequate for certain engineering problems, such as hypersonic flow and detonation physics with the existence of strong shock wave. The RANS equations combined with the one equation Spalart-Allmaras (SA) model without transition terms will be solved numerically.
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