2.4米跨声速风洞大展弦比飞机测力试验技术研究  

The test technique for aircraft with high aspect ratio in the 2.4 meter transonic wind tunnel

作　　者：陈德华[1] 尹陆平[1] 吴文华[1] 李建强[1] 师建元[1] 彭云[1] 

机构地区：[1]中国空气动力研究与发展中心空气动力学国家重点实验室,四川绵阳622661

出　　处：《空气动力学学报》2009年第5期542-546,共5页Acta Aerodynamica Sinica

摘　　要：针对大展弦比飞机的气动布局特点,在2.4米跨声速风洞中开展了大展弦比飞机测力试验技术研究。该项研究建立了大升阻比高精度天平设计技术和模型支撑系统设计平台,研制了专用大升阻比高精度测力天平和模型支撑系统。在国内高速风洞中建立了大型跨声速风洞模型设计新准则。研究结果表明:所提出和制定的方案是科学合理的,为我国大飞机研制提供了可靠的技术支撑。Aimed at characteristics of the aerodynamic configuration of aircraft with high aspect ratio, a test technical research for aircraft with high aspect ratio is conduced in the 2.4 meter transonic wind tunnel. A technique is sucessfully developed to design the high precise balance of high Lift-Drag ratio and a platform is made to design the model support system. A new regulation for the testing model designation is establi shed. The test result shows that the research is successful and the scheme used in the research is reasonable and scientific. The research provides reliable technique support for the development of large aircraft.

关 键 词：跨声速风洞 飞机 测力试验技术 天平 

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]