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• W2896661939 abstract "An array of 26 plasma synthetic jet actuators (PSJA) is flush-mounted on a NACA-0015 airfoil model to control the leading-edge flow separation at moderate Reynolds number ( $$Re_c=1.7times 10^5$$ ). The stall angle of this airfoil is postponed from $$15.5^circ$$ to approximately $$22^circ$$ , and the peak lift coefficient is increased by 21%. PSJAs exhibit distinctive separation control mechanisms depending on the relative location between actuation and separation and reduced frequency of actuation ( $$F^*$$ ). At an angle of attack of $$alpha =15.5^circ$$ , the non-actuated flow separates approximately $$4%$$ chord length downstream of the jet orifices . Plasma synthetic jets (PSJs) applied at $$F^*ge 0.5$$ can displace the separation point downstream to mid-chord position, as a result of the energizing of the incoming boundary layer through mixing enhancement. As a comparison, with actuation frequency of $$F^*le 0.25$$ , the separation point at $$alpha =15.5^circ$$ remains near the leading edge and the zero-velocity line is periodically swept towards the suction surface by the convecting spanwise vortices generated from PSJ actuation, leading to a reduction of time-averaged backflow area. For the case of separation control at $$alpha =22^circ$$ , the separation point resides always upstream of the actuation position, regardless of actuation frequency. The peak lift coefficient is attained at $$F^*=1$$ , and the decreasing lift at high actuation frequency ( $$F^*=2$$ ) is ascribed to the severe interaction between adjacent spanwise vortices at short spacing." @default.
• W2896661939 created "2018-10-26" @default.
• W2896661939 creator A5055051075 @default.
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• W2896661939 date "2018-10-15" @default.
• W2896661939 modified "2023-10-02" @default.
• W2896661939 title "Airfoil flow separation control with plasma synthetic jets at moderate Reynolds number" @default.
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• W2896661939 doi "https://doi.org/10.1007/s00348-018-2624-y" @default.
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