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首页> 外文会议>4th European Symposium on Aerothermodynamics for Space Vehicles, Oct 15-18, 2001, Capua, Italy >CALCULATION OF FLOWS CHARACTERIZED BY EXTENSIVE CROSS FLOW SEPARATION
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CALCULATION OF FLOWS CHARACTERIZED BY EXTENSIVE CROSS FLOW SEPARATION

机译：广泛的交叉流分离特征化的流量计算

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Flows with extensive cross flow separation appear in many flight vehicle configurations. Traditionally these types of flows are difficult to simulate accurately, especially if the separation is extensive (flow at high incidence or strong swept shock waves impinging on boundary layers). The present author has shown in previous publications that if the 3-D structure of these flows is considered for modifying a conventional turbulence model, the efficiency of the model is enhanced considerably. This concept has been demonstrated for the case of the supersonic fin/plate interaction, and it is based on the observation that in turbulent flows characterized by extensive cross-flow separation, a layer of low-turbulence exists close to the surface (underneath the core of the separation vortex). This flow feature has been incorporated in the Balwin-Lomax algebraic turbulence model by the introduction of a new relation for the calculation of the eddy viscosity within the separation domain. In the present paper the modified turbulence model is extended for application to more complicated shock wave/turbulent boundary layer interactions (crossing shocks) and to high-angle-of-attack flows.
机译：具有广泛的错流分离的气流出现在许多飞行器配置中。传统上，这些类型的流很难精确模拟，尤其是在分离范围大的情况下（高入射流或强冲击波冲击边界层时）。本作者在先前的出版物中已经表明，如果考虑将这些流的3-D结构用于修改常规湍流模型，则该模型的效率将大大提高。该概念已在超音速翅片/板相互作用的情况下得到证明，它基于以下观察结果：在以广泛的错流分离为特征的湍流中，靠近表面（在核心下方）存在一层低湍流分离旋涡的通过引入新的关系来计算分离域内的涡流粘度，该流动特征已被纳入Balwin-Lomax代数湍流模型。在本文中，改进的湍流模型被扩展以应用于更复杂的冲击波/湍流边界层相互作用（交叉冲击）和高攻角流。

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