Dynamic Actuation for Delta Wing Post Stall Flow Control
Dynamic Actuation for Delta Wing Post Stall Flow Control
复制标题
Delta 翼失速后流量控制的动态驱动
DOI：
10.1007/978-3-319-27279-5_72
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发表时间：
2016
影响因子：
5.6
通讯作者：
C. Breitsamter
中科院分区：
文献类型：
--
作者：
A. Kölzsch;S. Blanchard;C. Breitsamter
通过主动和被动流动控制方法来操纵三角翼流动对于提高此类配置的性能（例如升力增强）非常有意义。这项工作展示了在具有尖锐前缘的后掠通用半三角翼配置（VFE-2 几何结构）上，在非常高攻角（\(\alpha =\) 35–\(45^\circ \)）的失速后状态下的实验结果，该结构使用狭缝执行器沿前缘进行脉冲吹气。该研究包括力、速度和压力测量结果，并证实了剪切层对脉冲激励的接受能力。对于 \(\alpha = 35^\circ \)，\(F^{+} \approx 2.7\) 处的驱动会延迟涡流破裂。对于\(\alpha = 45^\circ \)，最佳脉冲频率在\(F^{+} =\) 1.0~1.5，这会导致爆发涡的重新建立和升力的显着增加，从而满足增强气动性能的目的。
The manipulation of delta wing flow by active and passive flow control methods is of great interest for increasing the performance (e.g. lift enhancement) of such configurations. This work presents experimental results in the post-stall regime at very high angles of attack (\(\alpha =\) 35–\(45^\circ \)) on a \(65^\circ \) sweptback generic half delta wing configuration (VFE-2 geometry) with sharp leading edge using slot actuators for pulsed blowing along the leading edge. The study comprises results of force, velocity and pressure measurements and substantiates the receptivity of the shear layer for the pulsed excitation. For \(\alpha = 35^\circ \), an actuation at \(F^{+} \approx 2.7\) effects a retardation of vortex breakdown. For \(\alpha = 45^\circ \), the optimum pulse frequency was found at \(F^{+} =\) 1.0–1.5, which leads to the re-establishment of a burst vortex and a significant increase in lift, thus satisfying the aim of enhancing aerodynamic performance.
影响因子：
2.2
作者：
Kölzsch;Breitsamter
通讯作者：
Breitsamter