Analyses of the lift-to-drag ratio and the efficiency parameter reveal that the dual excitation case is the most efficient stall control technique.
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#Airfoil generator hotwire full#
However, dual excitation is promising for a full stall control in a wide range of excitation frequencies. In addition, using the plasma actuator at the trailing edge solely is an ineffective flow separation control strategy. Accordingly, the first case prevents the stall phenomenon only at the wake mode frequency and its first super-harmonic.
![airfoil generator hotwire airfoil generator hotwire](https://i.ytimg.com/vi/WYATLSZKoUk/maxresdefault.jpg)
Moreover, the actuators energy consumption is evaluated for the controlled cases and a new efficiency parameter is presented. The vortex genera-tors are 40mm long, 10mm tall and 0.5mm thick. 19 added with triangular vortex generators Fig. The tested model consists of a 42cm chord and 80cm span wing with an Eppler 387 Fig. The results of the pressure coefficient distributions, as well as the aerodynamic coefficients, are compared for all cases. Figure 1: Test experiments of the airfoil into the wind tunnel. Further, in the third case, both of the actuators are utilized to excite the separated shear layers on the suction side and the trailing edge, simultaneously. In the second case, plasma actuation is applied to the shear layer at the trailing edge. In the first case, the frequency of natural vortex shedding and its different harmonics are employed to excite the suction side separated shear layer. Based on the active actuators, three controlled cases are considered in the present study. Two plasma actuators, one on the suction side just upstream the separation point and the other on the pressure side at the trailing edge, are exploited to control the baseline flow. The FFT spectra at four angles of attack ( 10, 12, 14, and 16) are investigated in Fig. Further, the dominant natural frequencies associated with flow structures in the airfoil wake are examined utilizing a hot-wire anemometer. The hot-wire anemometer probe is set at x / c 0.2 and y / c 0.03 from trailing edge in the airfoil wake region. To analyze the baseline flow, Time-averaged pressure distributions on the airfoil surfaces are evaluated with 40 pressure taps. This novel approach is studied experimentally on the NACA 0015 airfoil at the angle of attack and Reynolds number of 14° and 0.3 × 10 6, respectively.
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This paper investigates the stall control over an airfoil employing dual excitation of separated shear layers with dielectric barrier discharge plasma actuators.