Wind Tunnel and Free-Flight Testing of Active Flow Control for Modified NACA 613-618 Airfoil

Dianics, James V.; Balthazar, Michael; Groß, Andreas; Fasel, Hermann F.

doi:10.2514/6.2013-2516

Cited by 4 publications

(9 citation statements)

References 10 publications

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“…The ultimate goal of the research project was to transition AFC strategies from the wind tunnel experiments and simulations to flight hardware. As an intermediate step toward an AFC implementation on full-size aircraft, two wing gloves were developed for the free-flight testing of the AFC technology on the 1:5 scale AMT 200S models (Dianics et al [37,38]). A computer-aided [31,33]).…”

Section: Flight Experiments With Wing Glovesmentioning

confidence: 99%

“…Due to concerns related to electromagnetic interference with the radio flight control, DBD actuators were not being considered for the flight experiments. For the first wing glove, 16 Knowles Electronics EC Series 400 Ohm magnetic speakers with a sound pressure of 120 dB and a frequency range of 200 Hz-4 kHz were mounted at 5% chord (Figure 9) at a spanwise spacing of 1 cm [37]. Above each speaker, a 0.5-mm wide hole was drilled through the wing glove skin to allow the sound waves to exit.…”

Section: Flight Experiments With Wing Glovesmentioning

confidence: 99%

“…However, even with extensions, the lift curve slope is reduced compared to the wind tunnel experiments, and the maximum lift coefficient (at stall) is lowered. The dashed green and orange lines in Figure 40 [37]) superimposed with curve fits for minima and maxima with extensions and wind tunnel lift curves for Re = 137,000 and 322,000.…”

Section: Free-flight Experiments-wing Glovementioning

confidence: 99%

“…Overall, the disturbance levels are much lower than in the wind tunnel experiments (Figures 37-39) due to the low free-stream turbulence intensity in the flight experiments. [37]) superimposed with curve fits for minima and maxima with extensions and wind tunnel lift curves for Re = 137,000 and 322,000.…”

Section: Free-flight Experiments-wing Glovementioning

confidence: 99%

“…Wing-glove schematic with pressure tap (triangles) and actuator locations (square). (Reprinted by permission of the American Institute of Aeronautics and Astronautics, Inc. (Reston, VA, USA) from[37]).…”

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confidence: 99%

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Active Control of Laminar Separation: Simulations, Wind Tunnel, and Free-Flight Experiments

Groß

Fasel

2018

Aerospace

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When a laminar boundary layer is subjected to an adverse pressure gradient, laminar separation bubbles can occur. At low Reynolds numbers, the bubble size can be substantial, and the aerodynamic performance can be reduced considerably. At higher Reynolds numbers, the bubble bursting can determine the stall characteristics. For either setting, an active control that suppresses or delays laminar separation is desirable. A combined numerical and experimental approach was taken for investigating active flow control and its interplay with separation and transition for laminar separation bubbles for chord-based Reynolds numbers of Re ≈ 64,200–320,000. Experiments were carried out both in the wind tunnel and in free flight using an instrumented 1:5 scale model of the Aeromot 200S, which has a modified NACA 643-618 airfoil. The same airfoil was also used in the simulations and wind tunnel experiments. For a wide angle of attack range below stall, the flow separates laminar from the suction surface. Separation control via a dielectric barrier discharge plasma actuator and unsteady blowing through holes were investigated. For a properly chosen actuation amplitude and frequency, the Kelvin–Helmholtz instability results in strong disturbance amplification and a “roll-up” of the separated shear layer. As a result, an efficient and effective laminar separation control is realized.

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