等离子体激励抑制翼型失速分离的实验研究  

Experimental investigation on airfoil stall separation suppression by plasma actuation

作　　者：李应红[1] 吴云[1] 张朴[1] 苏长兵[1] 宋慧敏[1] 

机构地区：[1]空军工程大学飞机推进系统军队重点实验室,陕西西安710038

出　　处：《空气动力学学报》2008年第3期372-377,共6页Acta Aerodynamica Sinica

基　　金："863计划"资助项目:等离子体扩稳技术研究(2004AA753025)

摘　　要：进行了低速、低雷诺数条件下等离子体激励抑制NACA0015翼型失速分离的实验研究,研究了等离子体激励电压、激励电极数目和激励位置对流动分离抑制效果的影响。在翼型吸力面敷设不对称电极布局的等离子体激励器。在来流速度为4.27m/s,雷诺数为4.96×104的情况下,未施加等离子体激励时,从攻角为9°起翼型吸力面发生显著的前缘流动分离;施加等离子体激励后,流动分离在攻角小于26°的情况下均能很好地重附到翼型吸力面表面。实验表明,流动分离越严重,对等离子体激励的强度要求也越高,等离子体激励的电压和电极组数也必须相应增大;给定的流动分离状态下,等离子体激励的电压和电极组数存在一个阈值;等离子体激励的最佳位置在流动分离起始点的前缘;雷诺数增大后,流动分离更难抑制。Experimental investigation of plasma actuation based on NACA 0015 airfoil stall separation suppression is performed under low Reynolds number conditions. Research on how plasma actuation voltage, number of actuated electrode couples, actuation position and Reynolds number affect the flow separation suppression effect is done. Plasma actuator with asymmetric electrode distribution was laid on the airfoil suction surface. When the inflow velocity is 4.27m/s and corresponding Reynolds number is 4.96 × 10^4, obvious leading edge flow separation occurs on the airfoil suction surface since the angle of attack is 9° under no plasma actuation condition. Flow separation can reattach when the angle of attack is below 26° under plasma actuation. Experimental results indicated that, plasma actuation magnitude need to be higher when the flow separation becomes more serious, while the actuation voltage and actuated electrode couple number should be higher correspondingly. At a certain flow separation state, there are threshold values of plasma actuation voltage and couple number. The best position of plasma actuation is just the leading edge of flow separation origin line. When the Reynolds number becomes larger,flow separation becomes even harder to be suppressed.

关 键 词：航空 航天推进系统 等离子体激励 翼型 失速分离 流动控制 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]