摘要
为了提高等离子体气动激励控制附面层的能力,进行了脉冲等离子体气动激励抑制NACA 0015翼型失速分离的实验,研究了等离子体气动激励电压、位置、占空比和脉冲频率等对流动分离抑制效果的影响。在来流速度为72m/s时,等离子体气动激励可以有效地抑制翼型吸力面的流动分离,翼型的升力增大约35%,翼型的临界失速迎角由18°增大到21°。实验结果表明:分离越严重,来流速度越大,有效抑制翼型失速分离的阈值电压越大;等离子体气动激励的最佳位置在流动分离起始点的前缘;调节占空比,可以在控制效果相当的情况下,降低等离子体气动激励所消耗的功率;当脉冲频率使斯特劳哈尔数等于1时,控制效果最佳。
Experimental investigation of NACA 0015 airfoil stall separation suppression by plasma aerodynamic actuation is performed for the sake of improving the flow control capability of plasma aerodynamic actuation. Research on how plasma actuation voltage, actuation position, duty cycle and pulse frequency affect the flow separation suppression effect is done. It is found that when the inflow velocity is 72 m/s, plasma aerodynamic actuation can effectively suppress flow separation on the suction side of the airfoil, which causes a lift augment of 35%. The stall angle of the airfoil increases from 18° to 21°. Experimental results indicate that the thres hold voltage becomes higher as the inflow velocity becomes higher and the flow separation becomes more serious. The best position of plasma aerodynamic actuation is right at the leading edge of the flow separation origin line. Power consumption can be reduced by adjusting the duty cycle for equivalent control effects. The best control effect is obtained when the Strouhal number becomes one achieved by adjusting pulse frequency.
出处
《航空学报》
EI
CAS
CSCD
北大核心
2008年第6期1429-1435,共7页
Acta Aeronautica et Astronautica Sinica
基金
国家"863计划"(2005AA753031)
教育部优秀人才支持计划
空军工程学院优秀博士学位论文创新基金(BC07001)
