期刊文献+

γ-Re_(θt)-CF转捩模型在Spalart-Allmaras湍流模型中的推广及验证 被引量:6

Genevalization and validation of γ-Re_(θt)-CF transition modeling in combination with Spalart-Allmaras turbulence model
原文传递
导出
摘要 横流(CF)不稳定性是三维流动中诱发转捩的一项非常重要的因素,考虑到γ-Reθt-CF转捩模型对流向Tollmien-Schlichting波和横流波不稳定性引起转捩的判定均是完全基于当地变量,且Spalart-Allmaras(SA)湍流模型计算效率高,因而将γ-Reθt-CF转捩模型与SA湍流模型相结合,并将其引入开源Standford University Unstructured(SU2)计算流体力学分析平台。为了考察和验证模型的预测精度,分别使用原始γ-Reθt模型和γ-Reθt-CF-SA模型,对NLF(2)-0415后掠翼型和标准6∶1椭球模型进行了转捩预测数值模拟。算例结果表明,γ-Reθt-CF-SA模型的计算结果与试验数据吻合程度远远优于原始γ-Reθt模型,γ-Reθt-CF-SA模型能正确地预测出三维流动中的横流不稳定性引起转捩的现象。 One of the major 3Dtransition mechanisms is transition due to crossflow(CF)instability.Theγ-Re_(θt)-CF transition model is a local correlation-based approach for prediction of transition caused either by Tollmien-Schlichting steamwise instability or crossflow instability.In order to improve the efficiency,γ-Reθt-CF-SA model is coupled with the one-equation Spalart-Allmaras(SA)turbulence model,and is then implemented in open-source Standford University Unstructured(SU2),aplatform for computational fluid dynamics analyses.In order to validate and assess prediction accuracy of new model,a series of transition flows are simulated including NLF(2)-0415 swept airfoil and 6:1prolate spheroid standard model.Computation results usingγ-Reθt-CF-SA model are in good agreement with available experimental data,far superior to those using originalγ-Reθtmodel.Model proposed can effectively predict location of crossflow instability transition.
出处 《航空学报》 EI CAS CSCD 北大核心 2017年第4期66-74,共9页 Acta Aeronautica et Astronautica Sinica
关键词 转捩模型 横流不稳定性 基于当地变量 动量厚度 间歇因子 transition model crossflow instability local correlation-based momentum thickness intermittency
  • 相关文献

参考文献4

二级参考文献62

  • 1朱自强,王晓璐,吴宗成,陈泽民.民机设计中的多学科优化和数值模拟[J].航空学报,2007,28(1):1-13. 被引量:17
  • 2苏彩虹,周恒.零攻角小钝头钝锥高超音速绕流边界层的稳定性分析和转捩预报[J].应用数学和力学,2007,28(5):505-513. 被引量:25
  • 3苏彩虹,周恒.Stability analysis and transition prediction of hypersonic boundary layer over a blunt cone with small nose bluntness at zero angle of attack[J].Applied Mathematics and Mechanics(English Edition),2007,28(5):563-572. 被引量:3
  • 4Menter FR, Langtry RB, Likki SR. A correlation based transition model using local variables: part 1 model formulation. ASME-GT2004-53452, ASME TURBO EXPO 2004, Vienna, Austria, 2004.
  • 5Waiters DK, Leylek JH. Impact of film-cooling jets on turbine aerodynamic losses. ASME Journal of Turbomachinery. 2000, 122:537-545.
  • 6Volino RJ. A new model for free-stream turbulence effects on boundary layers. ASME Journal of Turbomachinery, 1998, 120:613-620.
  • 7Stock HW, Haase W. Navier-Stockes airfoil computations with transition prediction including transitional flow regions. AIAA Journal, 1996, 38 (11): 2059-2066.
  • 8Mayle RE, Schulz A. The path to predicting bypass transition. ASME Journal of Turbornachinery, 1997, 119: 405-411.
  • 9Walker G J, Gostelow JP. Effects of adverse pressure gradients on the nature and length of boundary-layer transition. ASME Journal of Turbomachinery, 1990, 112:196-205.
  • 10Volino RJ. Separated flow transition under simulated lowpressure turbine airfoil conditions -- part 1: mean flow and turbulence statistics. ASME Paper No. 2002-GT-30236, 2002.

共引文献93

同被引文献83

引证文献6

二级引证文献24

相关作者

内容加载中请稍等...

相关机构

内容加载中请稍等...

相关主题

内容加载中请稍等...

浏览历史

内容加载中请稍等...
;
使用帮助 返回顶部