Numerical and Experimental Wind Tunnel and Flight Testing of Active Flow Control for Modified NACA 643-618 Airfoil

Dianics, James V.; Ohno, Duncan; Fuggmann, Stefan D.; Lay, Jonas; Heim, D. E.; Fasel, Hermann F.

doi:10.2514/6.2015-1705

Cited by 3 publications

(5 citation statements)

References 11 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%

“…For'the flow control experiments, the speakers were operated at the maximum allowed amplitude, and the frequency was varied to set the blowing ratio, B. The second wing glove housed equipment for generating steady wall-normal jets [38]. The air The second wing glove housed equipment for generating steady wall-normal jets [38].…”

Section: Flight Experiments With Wing Glovesmentioning

confidence: 99%

“…The second wing glove housed equipment for generating steady wall-normal jets [38]. The air The second wing glove housed equipment for generating steady wall-normal jets [38]. The air pressure was provided by a 0.7 liters Robart aluminum air tank with a maximum air pressure of 10 The second wing glove housed equipment for generating steady wall-normal jets [38].…”

Section: Flight Experiments With Wing Glovesmentioning

confidence: 99%

“…The air The second wing glove housed equipment for generating steady wall-normal jets [38]. The air pressure was provided by a 0.7 liters Robart aluminum air tank with a maximum air pressure of 10 The second wing glove housed equipment for generating steady wall-normal jets [38]. The air pressure was provided by a 0.7 liters Robart aluminum air tank with a maximum air pressure of 10 bar (Figure 11).…”

Section: Flight Experiments With Wing Glovesmentioning

confidence: 99%

“…The air pressure was provided by a 0.7 liters Robart aluminum air tank with a maximum air pressure of 10 bar (Figure 11). A servo-operated pressure regulator controlled the airflow through 12 The second wing glove housed equipment for generating steady wall-normal jets [38]. The air pressure was provided by a 0.7 liters Robart aluminum air tank with a maximum air pressure of 10 bar (Figure 11).…”

Section: Flight Experiments With Wing Glovesmentioning

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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Section: Flight Experiments With Wing Glovesmentioning

confidence: 99%

Section: Flight Experiments With Wing Glovesmentioning

confidence: 99%

Section: Flight Experiments With Wing Glovesmentioning

confidence: 99%

Section: Flight Experiments With Wing Glovesmentioning

confidence: 99%

Section: Flight Experiments With Wing Glovesmentioning

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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Hybrid Turbulence Model Simulations of Partially Stalled Airfoil Flow

Groß

Fasel

2016

AIAA Journal

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Numerical Investigations of Laminar Separation Bubbles Under the Influence of Periodic Gusts

et al. 2023

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Direct numerical simulations were performed to investigate the behavior of laminar separation bubbles subject to vertical gusts in an airfoil flow. Oscillating boundary-layer flows containing gusts—including unsteady pressure gradients—were prescribed via boundary conditions as well as forcing terms on a domain located in the upper rear section of a natural laminar flow airfoil. For this hybrid approach, unsteady Reynolds-averaged Navier-Stokes (URANS) simulations of the entire flowfield were carried out in conjunction with the so-called disturbance velocity approach, providing transient boundary conditions for the direct numerical simulation. A steady-state reference case with a Reynolds number of [Formula: see text] is compared and validated with results from wind tunnel experiments. Results of simulations at four different gust frequencies [Formula: see text] at the same amplitude [Formula: see text], each with and without additional disturbances to the boundary layer introducing oblique resonance, are presented and discussed in this paper. The time-dependent behavior of convective instability modes is evaluated by using the continuous wavelet transform and linear stability theory with an unsteady extension. Furthermore, the contribution of the absolute instability—which appears to be larger in the case of oscillating flow compared to the steady-state case—is discussed. Lock-in effects are identified at high gust frequencies.

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Numerical and Experimental Wind Tunnel and Flight Testing of Active Flow Control for Modified NACA 643-618 Airfoil

Cited by 3 publications

References 11 publications

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

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

Hybrid Turbulence Model Simulations of Partially Stalled Airfoil Flow

Numerical Investigations of Laminar Separation Bubbles Under the Influence of Periodic Gusts

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