A low-dissipation scheme based on OpenFoam designed for large eddy simulation in compressible flow

To improve the large eddy simulation鈥檚 ability of simulating complex flow fields in the scramjet, a low-dissipation solver has been developed based on the original compressible solver rhoCentralFoam within the free open source computational fluid dynamics software OpenFOAM platforms. In rhoCentralFoam, the central-upwind scheme of Kurganov and Tadmor (Kurganov-Tadmor scheme) is applied to capture the flow discontinuity, whose dissipation is too strong to resolve turbulence under finite resolution. The low-dissipation solver adopts a new hybrid scheme, which combines the dissipative Kurganov-Tadmor scheme with the nondissipative central scheme through the shock sensor, where the dissipative scheme is used to capture the flow discontinuity near shock wave and the central scheme is used to resolve the turbulence structure in the smooth flow area. In the framework of unstructured mesh algorithm, the central scheme is extended from linear order to forth order, which greatly reduces the dispersion error and weakens the oscillations near flow discontinuity. To keep the numerical stability of the central scheme, we adopt the skew-symmetric form of the convective term, which could be able to preserve the local kinetic energy and help keep the self-stability of central scheme without adding an explicit dissipative term. In addition, a low-storage TVD Runge-Kutta method for third order temporal discretization is newly implemented in the low-dissipation solver to make the time marching in order to meet the requirement of large eddy simulation. A series of benchmark problems, such as Sod shock tube test, Shu-Osher problem, Green-Taylor vortex evolution, and wall-bounded turbulence generation based on synthetic eddy method, are computed and compared to examine the low-dissipation solver鈥檚 ability of capturing flow discontinuity as well as resolving turbulence structure. The accuracy and stability of the low-dissipation solver are further validated against experimental data when the supersonic airstream flows past the flame holder structure in the scramjet model. 漏 2017, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved