SA和SST湍流模型对高超声速边界层强制转捩的适应性

doi:10.7527/S1000-6893.2014.0292

Abstract

Abstract:

Protuberances are widely used for the trip laminar-turbulent transition of boundary layers. A row of 1 mm height diamond and slop protuberances are installed on the compression surface of a hypersonic inlet model. High-order schemes are applied to simulating the forced-transition flows. The Spalart-Allmaras (SA) and shear stress transport (SST) turbulence models are investigated for this kind of flow. Quite a number of numerical tests are taken to examine to what extent grid sizes, compressibility corrections and spatial discrete schemes influence the numerical accuracy. It turns out that the computed results are well consistent with experimental results in the laminar region, while the computed heating transfer rates are much larger than experimental data in the turbulent region. The inconsistency is suspected to be caused by the vortex structure of forced transitional flows which are quite different from natural transitional flows. The abundant vortices in forced transitional boundary layers may degrade the effectiveness of turbulence models. According to the characteristics of vortex structures, a modification to the SST model is suggested for hypersonic turbulent boundary layers caused by forced transition. Numerical tests indicate that the modification can enhance the accuracy of computed heating transfer rates.

Key words: turbulence models, boundary layer transition, vortex generators, high-order schemes, compressibility corrections

CLC Number:

V211.3
O355

TU Guohua, YAN Zhenguo, ZHAO Xiaohui, MA Yankai, MAO Meiliang. SA and SST turbulence models for hypersonic forced boundary layer transition[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(5): 1471-1479.

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SA and SST turbulence models for hypersonic forced boundary layer transition

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