大展弦比飞机变翼展洞壁干扰试验与分析  

Experiment and Analysis of Wall Interference of Large Aspect Ratio Airplane with Variable Wing Span

作　　者：许新[1,2] 陈德华[1,2] 程克明[3] 刘大伟[1,2] 魏志[2] XU Xin;CHEN Dehua;CHENG Keming;LIU Dawei;WEI Zhi(State Key Laboratory of Aerodynamics,Mianyang,621000,China;High Speed Aerodynamics Institute,China Aerodynamics Research and Development Center,Mianyang,621000,China;College of Aerospace Engineering,Nanjing University of Aeronautics&Astronautics,Nanjing,210016,China)

机构地区：[1]空气动力学国家重点实验室,绵阳621000 [2]中国空气动力研究与发展中心高速空气动力研究所,绵阳621000 [3]南京航空航天大学航空学院,南京210016

出　　处：《南京航空航天大学学报》2019年第4期519-525,共7页Journal of Nanjing University of Aeronautics & Astronautics

基　　金：空气动力学国家重点实验室研究基金(SKLA2015-3-4)资助项目

摘　　要：为了掌握不同马赫数、不同展长条件下大展弦比飞机模型风洞试验壁面压力分布,为高速风洞试验中大展弦比飞机模型展长的设计准则提供依据,设计加工了一套可变翼展大展弦比飞机模型,在2.4 m跨声速风洞中进行了洞壁干扰试验。试验过程中,使用13根壁压管测量了洞壁压力分布,试验马赫数范围0.4~0.86,模型展长与试验段宽度比例为65%~90%。结果显示,大展弦比飞机模型展长超过临界值(70%试验段宽度)后,亚声速范围内洞壁压力会产生突变,跨声速洞壁压力变化不大;大展弦比飞机亚声速风洞试验模型展长必须严格限制,跨声速试验模型展长可适当放宽要求。In order to obtain the wall pressure distribution of large aspect ratio airplane’s wind tunnel experiment with variable Mach number and wing span,guideline of the large airplane’s wing span design is provided in high speed wind tunnel,a large airplane model with variable wing span is designed and the wall interference experiment is conducted in 2.4 m transonic wind tunnel.The wall pressure distribution is measured with 13 tubes in test section,while the Mach number ranges from 0.4 to 0.86.The ratio of model’s wing span and the test section’s width ranges from 65%to 90%.Results show that wall pressure would change suddenly when the wing span is larger than the critical value(70%width of test section)in subsonic,while the transonic results remain unchanged.The wing span of large aspect ratio airplane in the subsonic wind tunnel must be restricted while the transonic test model could be designed larger.

关 键 词：飞行器设计 大展弦比 风洞 洞壁干扰 

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]