超临界机翼跨音速颤振风洞试验研究  

Transonic flutter wind tunnel tests for an aircraft with a supercritical wing

作　　者：孙亚军[1] 梁技[1] 杨飞[1] 章俊杰[1] 

机构地区：[1]中国商飞上海飞机设计研究院强度设计研究部,上海201210

出　　处：《振动与冲击》2014年第4期190-194,共5页Journal of Vibration and Shock

摘　　要：某先进民用支线飞机采用超临界机翼设计,跨音速颤振特性是超临界机翼的重要关键技术之一。颤振模型风洞试验是民机研制阶段最有效的跨音速颤振特性适航验证试验。设计了某民机超临界机翼跨音速风洞颤振试验模型并进行颤振风洞试验,根据试验结果并结合亚音速颤振分析和压缩性数值分析,得到了超临界机翼的跨音速颤振压缩性修正曲线。研究表明,超临界机翼跨音速颤振速度最大压缩性修正系数较小,风洞试验结果与理论分析吻合较好,试验结果可以用于飞机的适航取证。An advanced regional jet was designed with a supercritical wing.The acquirement of transonic flutter characteristics was one of the key techniques of the supercritical wing.The wind tunnel test of a flutter model was the most effective test for civil aircraft airworthiness compliance.A transonic flutter test model was designed and used to study the transonic flutter of the wing through the wind tunnel model test.Meanwhile,the test results were used to evaluate the flutter numerical calculation results of the model including the results of its subsonic flutter calculation and lift slope analysis.Comparisons showed that the test results agree well with those of the theoretical numerical analysis and the maximum Mach effect factor is small.The test results were applicable to the aircraft airworthiness compliance certification.

关 键 词：超临界机翼 跨音速颤振模型 风洞试验 

分 类 号：V215.3[航空宇航科学与技术—航空宇航推进理论与工程]