Stochastic estimation of flow near the trailing edge of a NACA0012 airfoil
Stochastic estimation of flow near the trailing edge of a NACA0012 airfoil
复制标题
NACA0012 翼型后缘附近流量的随机估计
DOI：
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发表时间：
2011
期刊：
影响因子：
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通讯作者：
T. Hynes
中科院分区：
文献类型：
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作者：
A. Garcia;T. Hynes
一个随机估计技术已被应用到同时采集的速度和表面压力的数据作为一种工具，以确定壁面压力波动的来源。在雷诺数Rec = 2 × 105的NACA 0012翼型上进行了测量，基于翼型的弦，其中存在分离的层流边界层。本文通过对翼型表面压力脉动和边界层及尾迹中速度场的同时测量，研究了翼型后缘附近的壁面压力源。研究了表面压力产生的机理和流动结构。“准瞬时”的速度场的应用所产生的技术导致了对流表面压力产生的流动结构的时间的演变的图片，并揭示了有关壁面压力波动的来源，其性质和可变性的信息。这些源与来自翼型的TE的辐射噪声以及例如船体中遇到的振动问题密切相关。NACA0012翼型的弦长为30 cm，展弦比为1。
A stochastic estimation technique has been applied to simultaneously acquired data of velocity and surface pressure as a tool to identify the sources of wall-pressure fluctuations. The measurements have been done on a NACA0012 airfoil at a Reynolds number of Rec = 2 × 105, based on the chord of the airfoil, where a separated laminar boundary layer was present. By performing simultaneous measurements of the surface pressure fluctuations and of the velocity field in the boundary layer and wake of the airfoil, the wall-pressure sources near the trailing edge (TE) have been studied. The mechanisms and flow structures associated with the generation of the surface pressure have been investigated. The “quasi-instantaneous” velocity field resulting from the application of the technique has led to a picture of the evolution in time of the convecting surface pressure generating flow structures and revealed information about the sources of the wall-pressure fluctuations, their nature and variability. These sources are closely related to those of the radiated noise from the TE of an airfoil and to the vibration issues encountered in ship hulls for example. The NACA0012 airfoil had a 30 cm chord and aspect ratio of 1.