小展弦比飞翼标模尾部畸变影响试验研究  

Study on the distortion effect of flying wing in low speed wind tunnel

作　　者：金玲[1] 刘李涛[1] 祝明红[1] 孙传宝[1] 陈陆军[1] 

机构地区：[1]中国空气动力研究与发展中心低速空气动力研究所,四川绵阳622762

出　　处：《空气动力学学报》2016年第1期119-124,共6页Acta Aerodynamica Sinica

摘　　要：在飞翼布局模型风洞试验中,为实现尾部支撑需对模型进行尾部修形。为摸清飞翼布局模型局部外形畸变的影响规律,本文在FL-14风洞对某小展弦比飞翼布局原始模型和尾部外形畸变模型进行了试验研究,采用增量法获得了尾部外形畸变的影响规律,并与国内三座低速风洞的三种支撑装置的近/远场支架干扰进行了对比分析。研究结果表明:小侧滑角时,在小迎角范围内尾部畸变影响量显著大于支架干扰量,在中大迎角范围则与支架干扰量级相当;畸变横向影响量较大,且随侧滑角增大而增大。所以应对全机的试验结果进行正确的"畸变"修正,或对尾部畸变外形进行优化,以减小畸变的影响。Flying wing is becoming one of the ideal aerodynamic configurations for military and civil aircraft because of its excellent aerodynamic efficiency and stealth performance.In order to acquire the effect of local configuration distortion due to sting support,a test study on low aspect ratio flying wing based on incremental method is carried out in CARDC FL-14 low speed wind tunnel.Both the afterbody distortion model and the calibration model are tested to investigate the distortion effect by means of antitheses method,and the comparison among the results of other three low speed wind tunnels with near-field/far-field support interference are presented.It is shown that the distortion effect is significantly stronger than support interference at small angle of attack and equivalent at medium and high angle of attack as the side slip angle is small.The distortion effect is more important in lateral direction than longitudinal direction,and intensified with the increasing angle of side slip.Test results is needed to be corrected and local afterbody configuration be optimized to reduce distortion effect.

关 键 词：飞翼布局 畸变 支架干扰 试验 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]