Aerodynamic control of NACA 0021 airfoil model with spark discharge plasma synthetic jets  

作　　者：LIU RuBing NIU ZhongGuo WANG MengMeng HAO Ming LIN Qi 

机构地区：[1]State Key Laboratory of Aerodynamics, China Aerodynamics Research and Development Center [2]School of Physics and Mechanical & Electrical Engineering, Xiamen University [3]Fujian Key Laboratory of Plasma and Magnetic Resonance [4]Aerodynamics Research Institute, Aviation Industry Corporation of China

出　　处：《Science China(Technological Sciences)》2015年第11期1949-1955,共7页中国科学（技术科学英文版）

摘　　要：Spark discharge plasma synthetic jets(SPJs) have been used for the active flow control study on an NACA 0021 straight-wing model in a wind tunnel. The model forces and moments were measured using a six-component sting balance at a 20 m/s wind speed. The aim was to explore the SPJ's effect on airfoil aerodynamic by examining SPJ generators' position along the chordwise and the jet flow direction about the chord. Near the wing leading edge, two SPJ generators raised the stall angle by 2° and increased the maximum lift coefficient by 9%. The drag coefficient was decreased by 33.1%, and the lift-drag ratio was increased by 104.2% at an angle of attack above 16°. The rolling-moment coefficient was modified by 0.002, and the yawing-moment coefficient was changed by 0.0007 at angles of attack in the range of 0°–16°. The results showed that SPJs can control wing aerodynamic forces at a high angle of attack and moments at a low angle of attack.

关 键 词：plasma synthetic jet spark discharge NACA 0021 airfoil aerodynamic performance aerodynamic control 

分 类 号：V211.74[航空宇航科学与技术—航空宇航推进理论与工程]