| Budget Amount *help |
¥4,940,000 (Direct Cost: ¥3,800,000、Indirect Cost: ¥1,140,000)
Fiscal Year 2017: ¥1,300,000 (Direct Cost: ¥1,000,000、Indirect Cost: ¥300,000)
Fiscal Year 2016: ¥1,560,000 (Direct Cost: ¥1,200,000、Indirect Cost: ¥360,000)
Fiscal Year 2015: ¥2,080,000 (Direct Cost: ¥1,600,000、Indirect Cost: ¥480,000)
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| Outline of Final Research Achievements |
The improvement of thrust performance of multi-electrode plasma actuator was investigated. Small serration was added to the exposed electrode of the plasma actuator to weaken the non-uniform generation of the discharge. The effects of the frequency of the applied AC voltage, and the gap length between their exposed electrodes has also been analyzed. Based on the result of the experiment and numerical simulation, an optimal configurations and conditions of the multi-electrode plasma actuator was proposed. The performance of separation control of the actuator was optimized by the Efficient Global Optimization (EGO) with Multi Additional sampling (MAs). The location of the plasma actuator and its body force were explored their optimal values that results a maximum lift coefficient for NACA0012 airfoil model. The wind tunnel experiment, based on the knowledge of the numerical simulation, confirmed a decisive superiority of the multi-electrode plasma actuator for separation control.
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