Differential Reynolds Stress Modeling for Separating Flows by Bernhard Eisfeld

By Bernhard Eisfeld

This publication offers contemporary development within the program of RANS turbulence versions in response to the Reynolds tension delivery equations. a number of versions has been carried out by way of various teams into assorted circulate solvers and utilized to exterior in addition to to faster equipment flows.

Comparisons among the versions enable an overview in their functionality in several circulate stipulations. the consequences exhibit the overall applicability of differential Reynolds tension versions to setting apart flows in commercial aerodynamics.

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Model, the initial solutions of the mean-flow equations (MF) and of the turbulence model equations are uniform and are based on freestream values. However, when using the MCL or the GLVY models, the initial solution is based on the converged solution obtained from the simulation using the SSG/LRR-! model. This is due to the anomaly of low-Reynolds "-based RANS turbulence model as was analyzed by Rumsey et al. [24]. The criteria of convergence was the reduction of the mean-flow residual by six orders in magnitude.

Int J Heat Fluid Flow 51:195–220 20. Menter FR (1994) Two-equation eddy-viscosity turbulence models for engineering applications. AIAA J 32(8):1598–1605 21. Mor-Yossef Y (2014) Unconditionally stable time marching scheme for Reynolds stress models. J Comput Phys 276:635–664 22. Probst A, Radespiel R (2008) Implementation and extension of a near-wall Reynolds-stress model for application to aerodynamic flows on unstructured meshes. AIAA paper 2008-770, 46th AIAA aerospace sciences meeting and exhibit, Reno NV 23.

Most CFD codes compute the cases using symmetry boundary conditions at the wing root, which likely introduces some error when comparing to experiment, particularly over the inner portion of the wing. This same approximation was used here. L. Rumsey The semi-span length of the ONERA M6 wing (not including rounded tip) was 1:1963 m. The most widely computed case has been at the conditions of ˛ D 3:06ı , M D 0:84, ReMAC D 11:72 106 , where the mean aerodynamic chord (MAC) is 0:64607 m. Although not shown, this same low angle-of-attack case was also computed for this study using SA, SST, EASMko2003-S, WilcoxRSM-w2006, and SSG/LRR-RSM-w2012.

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