几种常用格式和湍流模型在高速流动中的适用性研究  

Applicability investigation about several common schemes and turbulence models in high speed flow

作　　者：石磊[1] 闫溟[1] 杨云军[1] 周伟江[1] 

机构地区：[1]中国航天科技集团公司中国航天空气动力技术研究院,北京100074

出　　处：《航空动力学报》2014年第8期1904-1910,共7页Journal of Aerospace Power

摘　　要：针对高超声速飞行器中存在的强激波、激波/边界层干扰、分离、湍流等复杂流动现象,对比分析了当前计算流体力学中的主要空间离散格式及湍流模型,发现不同格式对强激波的分辨率基本相同,Roe和LDE(low diffusion E-CUSP(convective upwind split pressure))格式对摩擦因数和传热系数的模拟优于其他格式;S-A(Spalart-Allmaras)一方程湍流模型计算的摩擦因数比k-ωSST(shear stress transport)两方程湍流模型高10%左右,而后者预测的分离区约为前者的2倍,且分离点靠前.Several common spatial dispersion schemes and turbulence models in current computational fluid dynamics were compared and analyzed to investigate complex flow phenomenons such as strong shock waves, shock waves/boundary layer interaction, flow sepa- ration and turbulent flow in hypersonic flight. The results demonstrate that the resolutions of strong shock waves are the same by different schemes. Roe and LDE （low diffusion E- CUSP （convective upwind split pressure）） schemes show better agreement in friction coefficient and heat transfer coefficient with experimental data than other schemes. The friction coefficient predicted by S-A （Spalart-Allmaras） turbulence model is greater than that by/e-co SST （shear stress transport） turbulence model about 10%. The separation zone of the latter is twice the size of the former and the separation point is located in front.

关 键 词：高超声速 激波 边界层干扰 LDE格式 湍流模型 超声速凹槽 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]