小展弦比飞翼标模纵航向气动特性低速实验研究  

Low speed experiment on longitudinal and lateral aerodynamic characteristics of the low aspect ratio flying wing calibration model

作　　者：吴军飞[1] 秦永明[1] 黄湛[1] 魏忠武[1] 贾毅[1] 

机构地区：[1]中国航天空气动力技术研究院,北京100074

出　　处：《空气动力学学报》2016年第1期125-130,共6页Acta Aerodynamica Sinica

摘　　要：对小展弦比飞翼气动布局外形,通过常规测力风洞实验方法得到其纵向气动特性和偏航控制特性,在分析其气动特性后,选取典型的状态采用PIV实验方法对其流动机理进行研究,研究表明小展弦比飞翼在较小的迎角下即出现前缘分离涡,随着迎角的增大,前缘分离涡强度增大,且逐渐往机体对称面方向移动,随着迎角进一步增大,分离涡变得不稳定,涡核开始摆动,最终破裂,破裂位置从后缘开始,逐渐前移。对小展弦比飞翼气动布局飞机的控制难点偏航控制进行研究,结果表明该飞翼布局模型在实验迎角范围内偏航方向是静稳定的,在小迎角下具有可操纵性,迎角大于6°后嵌入面处于破裂的前缘涡尾迹之中,操纵性降低。longitudinal and lateral aerodynamic characteristics of the low aspect ratio flying wing calibration model are investigated in a low speed wind tunnel.Normal force measuring experiment is conducted to gain the longitudinal aerodynamic characteristics and yaw control characteristics,and the PIV test is also conducted to investigate the flow mechanism of the low aspect ratio flying wing.The results indicate that the leading-edge separation vortex appears on the wing＇s spine surface when the attack angle is at 6degree.The vortex intensity increases and the vortex core shifts to the symmetric plane of flying wing with the increase of attack angle.Increasing the attack angle further,the vortex core becomes unsteady and begins to oscillate,finally break entirely.The broken position shifts from the ending edge to the leading edge.Yaw control characteristics of low aspect ratio flying wing is also studied in this paper.The results indicate that the flying wing is static stabile at the test attack angle.When the attack angle is less than 6degree,it is controllable in yaw direction.And when attack angle is more than 6degree,the yaw control ability decreases because the control surface may lays in the wake region of broken leading-edge vortex.

关 键 词：小展弦比 飞翼 纵向气动特性 偏航控制 

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]