Lower drag and higher lift for turbulent airfoil flow by moving surfaces

Albers, Marian; Schröder, Wolfgang

doi:10.1016/j.ijheatfluidflow.2020.108770

Cited by 13 publications

(10 citation statements)

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“…It is important to acknowledge that, despite more than thirty years of intense research in this area of flow control, the optimistic results of large drag-reduction margins, even exceeding 50%, pertain to idealized scenarios. The future application of these methods to actual engineering systems is thus undoubtedly bound to be limited to lower levels of drag reduction, due to numerous factors, such as the impacts of the alteration of skin-friction drag on the other drag forms, mainly pressure drag and wave drag, of transonic flow, and of three-dimensionality and surface curvature [Albers and Schröder, 2021, Albers et al, 2019, Atzori et al, 2020.…”

Section: Future Research Directionsmentioning

confidence: 99%

A review of turbulent skin-friction drag reduction by near-wall transverse forcing

Riccó

Skote

Leschziner

2021

Progress in Aerospace Sciences

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Section: Future Research Directionsmentioning

confidence: 99%

A review of turbulent skin-friction drag reduction by near-wall transverse forcing

Riccó

Skote

Leschziner

2021

Progress in Aerospace Sciences

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“…While the transonic case resembles the incompressible one, at supersonic conditions, different trends in drag reduction are observed as well as a surprising relaminarization of the flow. LES of the flow over an airfoil equipped with spanwise oscillating walls is performed 152 where nearly 65% of both the upper and lower sides of the airfoil are fully actuated. The authors confirmed drag (and wall shear) reduction as well as lift increase.…”

Section: Classification and Description Of Flow Control Methodsmentioning

confidence: 99%

Current state and future trends in boundary layer control on lifting surfaces

Svorcan

Wang

Griffin

2022

Advances in Mechanical Engineering

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Successful flow control may bring numerous benefits, such as flow stabilization, flow reattachment, separation delay, drag reduction, lift increase, aerodynamic performance improvement, energy efficiency increase, shock delay or weakening, noise reduction, etc. For these purposes, many different flow control devices, which can be classified as passive, semi-active and active, have been designed and tested. This review paper aims to highlight the most promising and commonly employed boundary layer control methods as well as outline their potential in specific applications in aerospace and energy engineering. Referenced studies, performed on various geometries (flat plates, channels, airfoils, wings, blades, cylinders), are primarily numerical or experimental. Although enhanced aerodynamic performance is achieved in many cases, further research is required to draw general conclusions. This paper aims to demonstrate that, in the future, we may expect further developments of flow control actuators, as well as their increased application.

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Section: Introductionmentioning

confidence: 99%

“…Kornilov (2021) carried out an experimental study of blowing/suction on two-dimensional low-speed airfoils, and provided ideal estimates of the power spent for actuation. Albers & Schröder (2021) studied with implicit LES the same airfoil as considered by Atzori et al (2020), but controlled the flow via spanwise-travelling waves of wall-normal deformation. They generalised their previous results based on a different wing section (Albers, Meysonnat & Schröder 2019) and demonstrated that control alters both friction and pressure drag, thus improving the overall aerodynamic performance of the wing.…”

Section: Introductionmentioning

confidence: 99%

Drag reduction on a transonic airfoil

et al. 2022

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Flow control for turbulent skin-friction drag reduction is applied to a transonic airfoil to improve its aerodynamic performance. The study is based on direct numerical simulations (with up to 1.8 billion cells) of the compressible turbulent flow around a supercritical airfoil, at Reynolds and Mach numbers of $Re_\infty = 3 \times 10^{5}$ and $M_\infty =0.7$ . Control via spanwise forcing is applied over a fraction of the suction side of the airfoil. Besides locally reducing friction, the control modifies the shock wave and significantly improves the aerodynamic efficiency of the airfoil by increasing lift and decreasing drag. Hence, the airfoil can achieve the required lift at a lower angle of attack and with a lower drag. Estimates at the aircraft level indicate that substantial savings are possible; when control is active, its energy cost becomes negligible thanks to the small application area. We suggest that skin-friction drag reduction should be considered not only as a goal, but also as a tool to improve the global aerodynamics of complex flows.

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Lower drag and higher lift for turbulent airfoil flow by moving surfaces

Cited by 13 publications

References 50 publications

A review of turbulent skin-friction drag reduction by near-wall transverse forcing

A review of turbulent skin-friction drag reduction by near-wall transverse forcing

Current state and future trends in boundary layer control on lifting surfaces

Drag reduction on a transonic airfoil

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