空军工程大学学报（自然科学版）Issue(1)：6-9,4.DOI:10.3969/j.issn.1009-3516.2015.01.002
等离子体气动激励控制圆锥激波实验
Experimental Research on Plasma Actuation in Controlling Conical Shock
摘要
Abstract
In order to weaken conical shock strength around the aircraft head and the inlet adj ustment cone caused by supersonic flow,the experiment of plasma aerodynamic actuation in controlling conical shock is conducted.Variable laws of conical shock shape and in different excitation voltage conditions are performed by means of optical measurement and wall static pressure measurement.When the amplitude value of actu-ation voltage is 600V,800V,and 1000V respectively,the results show that when plasma aerodynamic ac-tuation conical shock shape is turned into 2 shocks,the shock wave angle is increased by 7.3°,13.2°,18.9° respectively and the cone head wall maximum total pressure is increased by 6.52%,8.17%,and 9.52% ac-cordingly.So,the fact that conical shock strength can be weakened by plasma aerodynamic actuation is verified.关键词
超声速流/流动控制/圆锥激波/等离子体气动激励Key words
supersonic flow/flow control/conical shock/plasma aerodynamic actuation分类
航空航天引用本文复制引用
程邦勤,王浩,孙权,胡伟波,陈志敏,李军..等离子体气动激励控制圆锥激波实验[J].空军工程大学学报（自然科学版）,2015,(1):6-9,4.基金项目
国家自然科学基金资助项目(51276197) （51276197）
