High-lift airfoil trailing edge separation control using a single dielectric barrier discharge plasma actuator |
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Authors: | Jesse Little Munetake Nishihara Igor Adamovich Mo Samimy |
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Institution: | (1) Gas Dynamics and Turbulence Laboratory, Department of Mechanical Engineering, The Ohio State University, 2300 West Case Road, Columbus, OH 43235, USA; |
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Abstract: | Control of flow separation from the deflected flap of a high-lift airfoil up to Reynolds numbers of 240,000 (15 m/s) is explored
using a single dielectric barrier discharge (DBD) plasma actuator near the flap shoulder. Results show that the plasma discharge
can increase or reduce the size of the time-averaged separated region over the flap depending on the frequency of actuation.
High-frequency actuation, referred to here as quasi-steady forcing, slightly delays separation while lengthening and flattening
the separated region without drastically increasing the measured lift. The actuator is found to be most effective for increasing
lift when operated in an unsteady fashion at the natural oscillation frequency of the trailing edge flow field. Results indicate
that the primary control mechanism in this configuration is an enhancement of the natural vortex shedding that promotes further
momentum transfer between the freestream and separated region. Based on these results, different modulation waveforms for
creating unsteady DBD plasma-induced flows are investigated in an effort to improve control authority. Subsequent measurements
show that modulation using duty cycles of 50–70% generates stronger velocity perturbations than sinusoidal modulation in quiescent
conditions at the expense of an increased power requirement. Investigation of these modulation waveforms for trailing edge
separation control similarly shows that additional increases in lift can be obtained. The dependence of these results on the
actuator carrier and modulation frequencies is discussed in detail. |
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