Numerical Studies of Active Flow Control Applied at the Engine-Wing Junction
Numerical Studies of Active Flow Control Applied at the Engine-Wing Junction
复制标题
发动机-机翼连接处主动流量控制的数值研究
DOI：
10.1007/978-3-319-21127-5_24
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发表时间：
2014
期刊：
影响因子：
--
通讯作者：
D. Norman
中科院分区：
文献类型：
--
作者：
S. Fricke;V. Ciobaca;J. Wild;D. Norman
本文提出了一种在发动机-机翼连接处应用主动流动控制以提高通用全尺寸风洞模型的增升性能的数值研究，该模型代表了发动机安装在后掠机翼下的常规客机的着陆布局。超高涵道比（UHBR）发动机的使用是目前进一步提高运输机效率的最有前途的方法之一。然而，它们的大发动机直径阻止了在发动机-机翼连接处安装前缘装置。这导致在短舱尾流中机翼吸力侧的局部气流分离，这可能触发机翼总失速，并因此损害高升力性能，从而损害飞机总效率。在德国航空航天中心（DLR）对发动机-机翼连接处的主动流动控制（AFC）进行了数值模拟，以研究抑制这种局部流动分离的能力。比较了具有相同致动器几何形状的稳态和脉冲射流吹扫的效果。结果表明，定常吹气减小了短舱-尾迹分离的尺寸。然而，所分析的装置的脉冲吹气显示出对短舱尾流分离的尺寸的低影响。
This paper presents a numerical study of active flow control applied at the engine-wing junction to increase the high-lift performance of a generic full scale wind tunnel model representing a landing configuration of conventional airliners with engines mounted under backward swept wings. The use of UHBR (Ultra High Bypass Ratio) engines is currently one of the most promising approaches to further increase the efficiency of transport aircraft. However their large engine diameter prevents the mounting of leading edge devices at the engine-wing junction. This leads to a local flow separation on the wing suction side in the wake of the nacelle which may trigger the total wing stall and hence compromises the high-lift performance and therefore the total aircraft efficiency. At DLR (German Aerospace Center) numerical simulations of AFC (active flow control) at the engine-wing junction were conducted to study the capability of suppressing this local flow separation. The effects of steady and pulsed jet blowing with the same actuator geometry are compared. The results show that the steady blowing reduces the size of the nacelle-wake separation. However the pulsed blowing of the analyzed setup shows a low effect on the size of the nacelle-wake separation.