机翼静气弹特性高速风洞试验研究  

Research on Static Aero-elastic Characteristics of Wing in High Speed Wind Tunnel

作　　者：杨波 江翔 马经忠 王国良 Yang Bo;Jiang Xiang;Ma Jingzhong;Wang Guoliang(AVIC Jiangxi Hongdu Aviation Industry Group Company Ltd.,Nanchang 330024,China)

机构地区：[1]航空工业江西洪都航空工业集团有限责任公司,江西南昌330024

出　　处：《气动研究与试验》2024年第4期82-86,共5页Aerodynamic Research & Experiment

摘　　要：在连续式跨声速风洞中对某大展弦比机翼的静气动弹性特性进行了试验研究。试验结果表明,静气动弹性对机翼气动特性有明显影响,可使机翼零迎角升力系数和升力线斜率降低;在不同马赫数下,静气动弹性对机翼焦点位置的影响表现出不同规律,在低亚声速时使机翼焦点位置后移,超过一定马赫数后,弹性影响使机翼焦点位置前移;设计巡航点的副翼效率降低约34%,弹性变形后的机翼剖面扭转角分布与设计目标值较为接近,验证了机翼型架外形设计的合理性。The static aeroelastic characteristics of a high aspect ratio wing were experimentally investigated in a continuous transonic wind tunnel.The test results show that the static aeroelasticity has a significant effect on the aerodynamic characteristics of the wing,which can reduce the lift coefficient at zero angle of attack and the lift curve slope.At different Mach numbers,the static aeroelasticity has different effects on the wing aerodynamic center position.At low subsonic speed,the wing focus position moves backward.When the Mach number exceeds a certain value,the elastic effect makes the wing focus position move forward.The aileron control efficiency at design cruise point is reduced by about 34% and the distribution of twist angle of wing profile after the elastic deformation is close to the design target value,which verifies the accuracy of wing rig shape design.

关 键 词：静气动弹性 弹性相似模型 大展弦比 副翼效率 

分 类 号：V211.71[航空宇航科学与技术—航空宇航推进理论与工程]