摘要
为研究飞翼布局模型在不同风洞的测力试验数据的相关性,分析飞翼布局模型风洞测力试验精度水平,为以融合体飞翼布局为代表的未来作战飞机气动力试验精度提供参考,采用同一台测力天平及外形相同的尾支杆在国内三座1.2m风洞中对小展弦比飞翼标模进行了重复性试验和对比试验。试验结果表明,小展弦比飞翼标模风洞测力试验精度及不同风洞数据相关性与飞翼布局流动特性关系较大,在小迎角附着流状态,不同风洞的数据相关性较好,测力精度较高,随着迎角的增加,飞翼布局背风面前缘涡会发生破裂,涡破裂后不同风洞的数据相关性和试验精度都有不同程度的降低。跨声速条件下由于飞翼布局背风面复杂的流动特性,使得其试验精度较超声速略差。不同风洞数据的差异主要体现在升力特性拐点起始迎角、近声速附近马赫数的零升阻力系数和零升迎角方面。
In order to investigate the correlation of force test results of flying-wing calibration model with low-aspect ratio and analyze the precision level of wind tunnel experiments in different wind tunnels,repeated tests and comparison tests on the flying-wing calibration model are conducted in three different wind tunnels based on a same balance and a set of stings with the same geometry.Test results indicate that the flow characteristics have huge influent on the correlation relations and the precision levels of the three wind tunnel test data.At small angels of attack when attached flow is dominant,the correlation of test data is good and the precision is high enough.However,as angles of attack increase and the leading-edge vortex will breakdown,both the correlation and the precision may fall down.Due to the complex flow characteristics at transonic flow,both correlation and precision are worse than that of supersonic flow.The main differences between test data of the three wind tunnels lie in the angle of attack of inflexion of the lift curve,zero-lift drag coefficient and zero-lift angle of attack.
出处
《空气动力学学报》
CSCD
北大核心
2016年第1期107-112,130,共7页
Acta Aerodynamica Sinica
关键词
飞翼布局标模
高速测力试验
重复性试验
精度
相关性
flying-wing calibration
high speed wind tunnel test
repeat test
precision
correlation
