article · Wind Engineering
Numerical investigations explore how integrating an injection-slot rotating cylinder at the leading edge affects the aerodynamic performance of the Go-Flow Jet CH10SM airfoil. Flow control techniques combining rotating cylinders with injection slots are relatively uncommon on airfoils. Aerodynamic coefficients were modelled across angles of attack ranging from 0 to 25 degrees using computational fluid dynamics software. Without the rotating cylinder mechanism, the maximum lift-to-drag ratio reached 18.256 with an injection guide vane slot slice and 13.693 without it at a 5-degree angle of attack. Incorporating the injection-slot rotating cylinder dramatically boosted performance, producing a lift-to-drag ratio of 223.036 for the base configuration and 229.536 with the slice at a 3-degree angle of attack. Operating the rotating cylinder with predominantly clockwise rotation directly enhanced the overall lift performance of the system.
Improving how airfoils generate lift while minimising drag is fundamental to aerodynamic efficiency. This research shows that combining active flow control methods, specifically leading-edge injection slots and rotating cylinders, can generate massive improvements in lift-to-drag efficiency at low angles of attack, offering new aerodynamic design pathways for advanced fluid dynamics applications.
This research could inform aerodynamic designs in sectors such as wind turbine blade engineering or aerospace flow control. Potential users include aerodynamic design engineers and turbine manufacturers looking to maximise energy capture or flight efficiency. Because the findings rely entirely on computational simulations, the technology remains at an early stage of research and would require physical prototyping and wind-tunnel testing before real-world adoption.
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This study numerically investigates the effect of an injection-slot rotating cylinder (ISRC) on the aerodynamic characteristics of the Go-Flow Jet (OGFJ)-CH10SM airfoil. However, the combined use of ISRC flow control techniques on airfoils remains limited. To address this challenge, a rotating cylinder is integrated with an injection slot over the airfoil’s leading edge. This work aims to improve the lift performance of the OGFJ-CH10SM airfoil by adding an ISRC. The Kutta-Joukowski theorem was used to compute coefficients from ANSYS 2025R1 simulations at angles of attack (AOA) from 0° to 25°. The results show that the maximum lift-to-drag ratios (LDR) are 18.256 for the injection guide vane slot slice and 13.693 without a slice at a 5° AOA. Furthermore, the OGFJ-CH10SM airfoil with ISRC achieves an LDR of 223.036, whereas the slice with ISRC achieves 229.536 at a 3° AOA. Therefore, the predominantly clockwise rotation of the ISRC proved beneficial for lift performance.
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DOI: 10.1177/0309524x261479504
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