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Active flow control for leading-edge vortex configurations

用于前沿涡流配置的主动流量控制

基本信息

批准号：
150836738
负责人：
Professor Dr.-Ing. Christian Breitsamter
金额：
--
依托单位：
Lehrstuhl für Aerodynamik und Strömungsmechanik
依托单位国家：
德国
项目类别：
Research Grants
财政年份：
2010
资助国家：
德国
起止时间：
2009-12-31 至 2017-12-31
项目状态：
已结题

来源：
https://gepris.dfg.de/gepris/projekt/150836738?language=en
关键词：
Active flow control leading edge

项目摘要

The flow around delta wing configurations is characterized by the formation of large-scale leading edge vortices, linked to attached and separated, laminar and turbulentshear layers. These flow structures are associated with unsteadiness over a broad range of scales and comprise non-linear interaction. From an aerodynamic point of view, influencing the characteristic vortex flow instabilities, namely those related to the rolling up shear layer and to vortex burtsing, is of great interest due to the possibility of increasing the performance of such configurations as well as the stability at the borders of the flight envelope. Here, periodic oscillations of sectional, leading-edge active flap elements and pulsed blowing using slanted slots near the leading edge are used to manipulate and control the vortex flow. Actuation frequencies are correlated to the frequencies of the flow instability mechanisms. The investigations are conducted for a generic delta wing geometry used in a previous research program (BR 1511/1) featuring a large experimental and numerical data base. This data base comprises the case of partly developed, fully developed and burst leading-edge vortices depending geometrically fixed or free primary separation and angle of attack. Flow control is aimed to increase the aerodynamic efficiency and longitudinal and lateral stability in the high angle-of-attack regime (stall and post-stall regime) and to reduce structural dynamic loads by alleviating unsteady aerodynamic loads.

围绕三角翼布局的流动的特征是形成大尺度前缘涡，与附着层和分离层、层流层和顺剪层相联系。这些流动结构与大范围尺度上的不稳定性相关，并且包括非线性相互作用。从空气动力学的观点来看，影响特征涡流不稳定性，即与卷起剪切层和涡流破裂有关的不稳定性，由于有可能提高这种布局的性能以及在飞行包线边界处的稳定性，因此是很有意义的。在这里，分段的周期性振荡，前缘主动襟翼元件和脉冲吹气使用前缘附近的斜槽被用来操纵和控制涡流。驱动频率与流动不稳定机制的频率相关。对以前研究计划（BR 1511/1）中使用的通用三角翼几何形状进行了研究，实验和数值数据库。该数据库包括部分发展、完全发展和破裂前缘涡的情况，这些情况取决于几何上固定的或自由的主分离和攻角。流动控制的目的是提高大迎角区（失速区和过失速区）的气动效率和纵向及横向稳定性，并通过减轻非定常气动载荷来减小结构动载荷。