Optimal Control of Shock Wave Turbulent Boundary Layer Interactions Using Micro-Array Actuation
Optimal Control of Shock Wave Turbulent Boundary Layer Interactions Using Micro-Array Actuation
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DOI：
10.2514/6.2006-3197
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发表时间：
2006-12
期刊：
影响因子：
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通讯作者：
B. H. Anderson;J. Tinapple;L. Surber
中科院分区：
文献类型：
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作者：
B. H. Anderson;J. Tinapple;L. Surber
本微阵列流动控制研究的目的是证明响应面方法（RSM）的可行性和经济性，以确定控制超音速进气道内激波湍流边界层相互作用的微阵列驱动优化设计，并将这些概念与传统的排流性能进行比较。术语微阵列是指微致动器阵列，其高度为无扰动超音速边界层厚度的25%至40%。本研究涵盖了在自由流马赫数为2.0时，使用标准微叶片、锥形微叶片和标准微斜坡阵列对激波湍流边界层相互作用的最优控制。利用10激波发生器引起的激波压力升，测试了三种微阵列器件的有效性，该激波压力升足以分离湍流超音速边界层。微阵列的总体设计目的是通过在近壁面区域引入一串反向旋转的微涡来改变超音速边界层的性质。这样可以使激波边界层（SWBL）相互作用对主流场的影响降到最低而不产生边界出血。
The intent of this study on micro-array flow control is to demonstrate the viability and economy of Response Surface Methodology (RSM) to determine optimal designs of micro-array actuation for controlling the shock wave turbulent boundary layer interactions within supersonic inlets and compare these concepts to conventional bleed performance. The term micro-array refers to micro-actuator arrays which have heights of 25 to 40 percent of the undisturbed supersonic boundary layer thickness. This study covers optimal control of shock wave turbulent boundary layer interactions using standard micro-vane, tapered micro-vane, and standard micro-ramp arrays at a free stream Mach number of 2.0. The effectiveness of the three micro-array devices was tested using a shock pressure rise induced by the 10 shock generator, which was sufficiently strong as to separate the turbulent supersonic boundary layer. The overall design purpose of the micro-arrays was to alter the properties of the supersonic boundary layer by introducing a cascade of counter-rotating micro-vortices in the near wall region. In this manner, the impact of the shock wave boundary layer (SWBL) interaction on the main flow field was minimized without boundary bleed.