Suppression of flow separation of a high-lift wing with active flow control

Qiangqiang Sun; Faycal Bahri; Mark Jabbal; Wit Stryczniewicz; Richard Jefferson-Loveday; Bruno Stefes; Alexander Buscher

doi:10.1016/j.ast.2025.110017

Suppression of flow separation of a high-lift wing with active flow control

Qiangqiang Sun, Faycal Bahri, Mark Jabbal^*, Wit Stryczniewicz, Richard Jefferson-Loveday^*, Bruno Stefes, Alexander Buscher

^*Corresponding author for this work

Engineering

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Abstract

Flow separation caused by the integration of a leading edge slat cut-out to accommodate an ultra-high bypass ratio engine reduces the maximum lift coefficient. In this study, an active flow control approach including 88 pulsed jet nozzles near the leading edge is used to control flow separation over a multi-element high-lift aerofoil. A hybrid large-eddy simulation (LES) and stress-blended eddy simulation (SBES) method is deployed to analyze flow physics and wind tunnel tests are also performed for the flow with/without control. The results show that severe flow separation is observed for the clean case by visualizing the streamlines on the airfoil's surface via numerical and experimental methods. Compared with the clean case, the stall angle is delayed by around 4°, and the maximum lift coefficient is increased by more than 15% after deploying the active flow control. Meanwhile, when the active flow control is imposed, a lift enhancement region caused by the vortex shedding downstream of the jet nozzles is formed adjacent to the leading edge, and its scale becomes larger along the spanwise direction.

Original language	English
Article number	110017
Number of pages	11
Journal	AEROSPACE SCIENCE AND TECHNOLOGY
Volume	159
Early online date	5 Feb 2025
DOIs	https://doi.org/10.1016/j.ast.2025.110017
Publication status	Published - Apr 2025

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Suppression of flow_SUN_Publishedonline5February2025_GOLD VoR (CC-BY)Final published version, 4.07 MBLicence: CC BY

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title = "Suppression of flow separation of a high-lift wing with active flow control",

abstract = "Flow separation caused by the integration of a leading edge slat cut-out to accommodate an ultra-high bypass ratio engine reduces the maximum lift coefficient. In this study, an active flow control approach including 88 pulsed jet nozzles near the leading edge is used to control flow separation over a multi-element high-lift aerofoil. A hybrid large-eddy simulation (LES) and stress-blended eddy simulation (SBES) method is deployed to analyze flow physics and wind tunnel tests are also performed for the flow with/without control. The results show that severe flow separation is observed for the clean case by visualizing the streamlines on the airfoil's surface via numerical and experimental methods. Compared with the clean case, the stall angle is delayed by around 4°, and the maximum lift coefficient is increased by more than 15% after deploying the active flow control. Meanwhile, when the active flow control is imposed, a lift enhancement region caused by the vortex shedding downstream of the jet nozzles is formed adjacent to the leading edge, and its scale becomes larger along the spanwise direction.",

author = "Qiangqiang Sun and Faycal Bahri and Mark Jabbal and Wit Stryczniewicz and Richard Jefferson-Loveday and Bruno Stefes and Alexander Buscher",

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year = "2025",

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doi = "10.1016/j.ast.2025.110017",

language = "English",

volume = "159",

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T1 - Suppression of flow separation of a high-lift wing with active flow control

AU - Sun, Qiangqiang

AU - Bahri, Faycal

AU - Jabbal, Mark

AU - Stryczniewicz, Wit

AU - Jefferson-Loveday, Richard

AU - Stefes, Bruno

AU - Buscher, Alexander

PY - 2025/4

Y1 - 2025/4

N2 - Flow separation caused by the integration of a leading edge slat cut-out to accommodate an ultra-high bypass ratio engine reduces the maximum lift coefficient. In this study, an active flow control approach including 88 pulsed jet nozzles near the leading edge is used to control flow separation over a multi-element high-lift aerofoil. A hybrid large-eddy simulation (LES) and stress-blended eddy simulation (SBES) method is deployed to analyze flow physics and wind tunnel tests are also performed for the flow with/without control. The results show that severe flow separation is observed for the clean case by visualizing the streamlines on the airfoil's surface via numerical and experimental methods. Compared with the clean case, the stall angle is delayed by around 4°, and the maximum lift coefficient is increased by more than 15% after deploying the active flow control. Meanwhile, when the active flow control is imposed, a lift enhancement region caused by the vortex shedding downstream of the jet nozzles is formed adjacent to the leading edge, and its scale becomes larger along the spanwise direction.

AB - Flow separation caused by the integration of a leading edge slat cut-out to accommodate an ultra-high bypass ratio engine reduces the maximum lift coefficient. In this study, an active flow control approach including 88 pulsed jet nozzles near the leading edge is used to control flow separation over a multi-element high-lift aerofoil. A hybrid large-eddy simulation (LES) and stress-blended eddy simulation (SBES) method is deployed to analyze flow physics and wind tunnel tests are also performed for the flow with/without control. The results show that severe flow separation is observed for the clean case by visualizing the streamlines on the airfoil's surface via numerical and experimental methods. Compared with the clean case, the stall angle is delayed by around 4°, and the maximum lift coefficient is increased by more than 15% after deploying the active flow control. Meanwhile, when the active flow control is imposed, a lift enhancement region caused by the vortex shedding downstream of the jet nozzles is formed adjacent to the leading edge, and its scale becomes larger along the spanwise direction.

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DO - 10.1016/j.ast.2025.110017

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JO - AEROSPACE SCIENCE AND TECHNOLOGY

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M1 - 110017

ER -

Suppression of flow separation of a high-lift wing with active flow control

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