地面试验模拟高空等离子体流动控制效果

doi:10.7527/S1000-6893.2014.0107

Abstract

Abstract:

The method which is used to study the plasma flow control performance at different altitudes by ground experiments is presented. The induced jet Reynolds number is measured in static air under different pressures at first, then the geometrical and electrical parameters of ground plasma model actuator will be obtained according to Reynolds similarity of the plasma induced jet. Secondly, the model actuator is applied to the wind tunnel experiments and the results can be used to estimate the plasma flow control performance at different altitudes. That plasma modifies the flowfield of S1223 airfoil is studied by this method. It is found that when the altitude increases, the maximal velocity of plasma induced jet increases but Reynolds number decreases under the same working conditions. The plasma can induce one high-speed normal jet towards wall above the actuator except the wall tangential jet under low pressure. The S1223 airfoil with Reynolds number 7.1×10⁴ controlled by the Reynolds similarity plasma model actuator is studied. It is found that when the angle of attack is 6°-20°, the lift coefficient increases about 27% to 43% which indicates that the lift performance of near space vehicle can be improved markedly by plasma.

Key words: plasma, flow control, ground experiment, induced jet, similarity

CLC Number:

V211

CHE Xueke, NIE Wansheng, HOU Zhiyong, HE Haobo, TIAN Xihui, TIAN Xuemin. High altitude plasma flow control simulation through ground experiment[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(2): 441-448.

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High altitude plasma flow control simulation through ground experiment

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