Steady Turbulent Flow Computations Using a Low Mach Fully Compressible Scheme

A recently proposed modification to fully compressible schemes significantly improves the resolution of low-Mach-number features, tackling the problem of excessive numerical dissipation as the Mach number reduces. This paper explores the application of this modification to Reynolds-averaged Navier–S...

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Bibliographic Details
Published in:AIAA journal 2014-11, Vol.52 (11), p.2559-2575
Main Authors: Garcia-Uceda Juarez, A, Raimo, A, Shapiro, E, Thornber, B
Format: Article
Language:English
Subjects:
Aerodynamics
Aerospace engineering
Backward facing steps
Boundary layer interaction
Compressibility
Computation
Computational fluid dynamics
Fluid dynamics
Fluid flow
Holes
Mach number
Mathematical models
Navier-Stokes equations
Numerical dissipation
Oblique shock waves
Solvers
Turbulence
Turbulent flow
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Summary:A recently proposed modification to fully compressible schemes significantly improves the resolution of low-Mach-number features, tackling the problem of excessive numerical dissipation as the Mach number reduces. This paper explores the application of this modification to Reynolds-averaged Navier–Stokes simulations using second- and fifth-order in-space schemes. Following verification of the modeling approach, four test cases are employed to highlight the scheme performance, including a backward-facing step, a two-dimensional lid-driven cavity, the NACA 4412 airfoil (incorporating a trailing-edge separation), and finally a Mach 2.25 oblique shock-wave–boundary-layer interaction. It demonstrates first that the converged solution is grid- and scheme-independent, as expected, and that the low-Mach-number correction provides a significant improvement in low-Mach-number regions. Because this correction is easy to implement, computationally inexpensive, and stable, the conclusion is that it should be recommended for all existing Godunov-type Reynolds-averaged Navier–Stokes solvers.
ISSN:0001-1452
1533-385X
DOI:10.2514/1.J052948