导弹大攻角绕流数值模拟中湍流模型确认研究  

Validation of Turbulence Model in Numerical Simulations of Missile Aerodynamics at High Angle of Attack

作　　者：李中武[1] 

机构地区：[1]中国航空计算技术研究所航空气动力数值模拟重点实验室,西安710068

出　　处：《航空兵器》2008年第5期7-11,共5页Aero Weaponry

摘　　要：通过数值求解雷诺平均N-S方程,采用S-A,SST和W&J CC EARSMHellstenk-ω三种湍流模型模拟了十字翼导弹在超声速大攻角下的流场。轴向及纵向站位的物面压力分布和实验数据的对比表明:湍流模型对物面压力分布影响较大,靠近壁面的二次分离涡的模拟精度和湍流模型密切相关。不同站位截面分离流线表明,空间主体涡结构受湍流模型影响不明显。The S-A, SST and W＆J CC EARSM Hellsten k - w turbulence models are applied to simulate the complex supersonic flow field around cruciform-wing missile body by solving the Reynold average N-S equation. Comparing the predicted pressure distribution numerical results of axial location and longitudinal location with the test data, the results show that the predicted pressure distribution is influenced by turbulence model greatly, and the analog precision of secondary vertices which near missile body is clearly related with turbulence model. The separate streamlines at different location show that the main vertical structure in flow field is influenced by the three turbulence models trivially.

关 键 词：湍流模型 分离涡 确认 十字翼导弹 

分 类 号：TJ760.11[兵器科学与技术—武器系统与运用工程]