Abstract
An experimental study on the circulation control around a modified NCCR1510-7067N airfoil is presented. The plasma-induced wall jet is achieved by the use of Dielectric Barrier Discharge plasma actuators, which are placed around the curved circular trailing edge. A wind tunnel test is performed in order to quantify the effects of applied voltage and actuator position on the lift enhancement. The lift and pressure measurements are taken using micro pressure electronic scanning valve. Additionally a smoke flow visualization test is performed in order to elucidate the fundamental working principles of the concept. Preliminary results indicate that the variation of the lift coefficient with the applied voltage was nonlinear, the short laminar separation bubble appeared at the leading edge in advance with applied voltages above 8 kV; consequently, the optimal applied voltage was 8 kV. The lift coefficient was increased by 0.154 and the lift augmentation efficiency reached 108.7 with a single actuator on the lower surface. A smoke flow visualization showed the delay of separation position and the formation of virtual flap effect.
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Zhang, Y., Zhang, D., Li, L., Zheng, W., Luo, H. (2019). Experimental Study on Aerodynamic Properties of Circulation Control Airfoil with Plasma Jet. In: Zhang, X. (eds) The Proceedings of the 2018 Asia-Pacific International Symposium on Aerospace Technology (APISAT 2018). APISAT 2018. Lecture Notes in Electrical Engineering, vol 459. Springer, Singapore. https://doi.org/10.1007/978-981-13-3305-7_79
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DOI: https://doi.org/10.1007/978-981-13-3305-7_79
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