Separation Control on a High-Lift Airfoil using Vortex Generator Jets at High Reynolds numbers

Casper, Marcus; Scholz, Peter; Radespiel, Rolf; Wild, Jochen; Ciobaca, Vlad

doi:10.2514/6.2011-3442

Cited by 13 publications

(8 citation statements)

References 11 publications

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“…Settling chamber volumes were recently reduced in contrast to the version of Casper et at. 8 It is expected that such a decrease of the volume accompanies a gain in accuracy of the jet frequency response signal. Fast switching, solenoid valves made by FESTO were used to allow for dynamically blowing.…”

Section: A Experimental Setupmentioning

confidence: 99%

“…For the studies described herein, a Reynolds number of 2 · 10 6 can be achieved, which is 3.5 times less, however, the influence of the Reynolds number has been studied by Casper et at. 8 Due to the small Reynolds number a small-scale laminar separation bubble is formed, which can result in a corresponding bubble-burst kind of stall. To prevent such laminar leading edge separation the transition was tripped by a thin 50µm tape (2mm x 0.8mm).…”

Section: A Experimental Setupmentioning

confidence: 99%

“…The active flow control system is basically of the same mechanism as used in previous investigations 6 . 8 The system consists of fast switching solenoid valves, settling chambers and orifices integrated in the leading edge box. The whole model was equipped with 34 valves.…”

Section: A Experimental Setupmentioning

confidence: 99%

“…A detailed overview over the design and stall behavior is given by Wild et al 6,7,12 Later, investigations including an active flow control system near the leading-edge show that a system of vortex generator jets can influence the stall behavior in a positive manner. Experiments 6,8 and numerical 9 studies were carried out at medium Reynolds numbers of 2.0 · 10 6 as well as at high Reynolds numbers up to 12.2 · 10 6 . For this work the AFC system consists of vortex generator jets integrated into the leading-edge to prevent a turbulent leading-edge stall.…”

Section: Introductionmentioning

confidence: 99%

See 3 more Smart Citations

Active flow control at a swept wing: A comparison of numerical and experimental results

Huehne

Mahmood

Scholz

2013

31st AIAA Applied Aerodynamics Conference

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This work focuses on a comparison of experimental results and numerical data of an active flow control system for a 3D two element high-lift airfoil at Reynolds numbers of 2.0 · 10 6 . The model is equipped with vortex generator jets close to the leading edge to suppress a turbulent leading edge stall. Comparison of the 3D experiments and different numerical cases including 2.5D and 3D calculations without AFC point out that the finding of the experiments can be reproduced quite well with a 2.5D-approach. However, full 3D computations give a better match with the experimental results. By a comparison of experimental and numerical (2.5D) data including the effect of active flow control it can be shown that the numerical approach successfully reproduces the effect of the vortex generator jets on the turbulent leading edge stall. In combination, the approach of 2.5D studies with active flow control and accompanying 3D full wing studies for the baseline cases does deliver all results necessary to assess the effectiveness of the active flow control system for a given configuration.

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Section: A Experimental Setupmentioning

confidence: 99%

Section: A Experimental Setupmentioning

confidence: 99%

Section: A Experimental Setupmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Active flow control at a swept wing: A comparison of numerical and experimental results

Huehne

Mahmood

Scholz

2013

31st AIAA Applied Aerodynamics Conference

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“…Pulsed blowing is employed to increase the wing model's aerodynamic efficiency by offsetting the increase in drag. The feasibility of preventing separation at the leading edge by AFC was demonstrated successfully in recent studies [4][5][6][7][8][9][10], which focused primarily on increasing the maximum lift and stall angle of slatless single-or multi-element airfoils. Research on localized flow control has also appeared in a multidisciplinary study from the aeronautical industry [11].…”

Section: Introductionmentioning

confidence: 99%

Wing Tip Drag Reduction at Nominal Take-Off Mach Number: An Approach to Local Active Flow Control with a Highly Robust Actuator System

Bauer¹,

Grund

Nitsche

et al. 2016

Preprint

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This paper discusses wind tunnel test results aimed at advancing active flow control technology to increase the aerodynamic efficiency of an aircraft during take-off. A model of the outer section of a representative civil airliner wing was equipped with two-stage fluidic actuators between the slat edge and wing tip, where mechanical high-lift devices fail to integrate. The experiments were conducted at a nominal take-off Mach number of M = 0.2. At this incidence velocity, separation on the wing section, accompanied by increased drag, is triggered by the strong slat edge vortex at high angles of attack. On the basis of global force measurements and local static pressure data, the effect of pulsed blowing on the complex flow is evaluated, considering various momentum coefficients and spanwise distributions of the actuation effort. It is shown that through local intensification of forcing, a momentum coefficient of less than c µ = 0.6% suffices to offset the stall by 2.4 • , increase the maximum lift by more than 10%, and reduce the drag by 37% compared to the uncontrolled flow.

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Efficient Design of Airfoil Employing XFLR for Smooth Aerodynamics of Drone

Verma

Kumar

Khanna

et al. 2021

Studies in Systems, Decision and Control

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Separation Control on a High-Lift Airfoil using Vortex Generator Jets at High Reynolds numbers

Cited by 13 publications

References 11 publications

Active flow control at a swept wing: A comparison of numerical and experimental results

Active flow control at a swept wing: A comparison of numerical and experimental results

Wing Tip Drag Reduction at Nominal Take-Off Mach Number: An Approach to Local Active Flow Control with a Highly Robust Actuator System

Efficient Design of Airfoil Employing XFLR for Smooth Aerodynamics of Drone

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