摘要
低雷诺数风洞实验中,相同雷诺数条件下,不同的风洞实验结果有较大区别。针对此现象进行了相同雷诺数条件下速度对流场结构的研究。首先,对低雷诺数翼型SD7037的数值计算方法进行了验证。然后保证计算雷诺数Re=300000,来流湍流度等条件不变,通过改变来流速度,选取10 km、15 km、20 km等3个海拔高度计算状态进行了计算,分析了不同计算高度状态下压力分布及绕流流场的变化。计算结果表明,随着计算高度的增加,流动分离点逐渐前移,升力系数增大,阻力系数也相应增大,升阻比减小。表明在相同雷诺数条件下,速度不同导致流动分离点的移动是影响气动特性的主要原因,为低雷诺数风洞实验及数值模拟提供了参考。
At low Reynolds number,different wind tunnel test results had great differences for the same Reynolds number conditions.In this paper,we studied the influence of velocity to flow field structure for the same Reynolds number.Firstly,the numerical simulation of low Reynolds number SD7037 airfoil was carried out to prove the accuracy of this method.Secondly,at Re=300000,the factors such as turbulence intensity were unchanged,the change of the pressure on airfoil and flow flied structure was analyzed at the 10km,15km and 20km three altitude calculation conditions.The results show that with the increasing of altitude and the flow velocity,the separation point moves forward gradually,it also results in the increasing of lift coefficient as well as the drag coefficient,the decreasing of L/D.The result also underlines that the movement of the flow separation point because of the changing of the velocity is the main factor affecting the aerodynamic characteristics for the same Reynolds number.And it provides a reference for the low Reynolds number wind tunnel experiment and numerical simulation.
作者
赵炜
高德亮
黄江流
尹航
周俊忠
ZHAO Wei;GAO De-liang;HUANG Jiang-liu;YIN Hang;ZHOU Jun-zhong(Shanghai Electro-Mechanical Engineering Institute,Shanghai 201109,China;First Military Representative Office of Air Force Equipment Department in Shanghai,Shanghai 201109,China;Shanghai Space Propulsion Technology Institute,Shanghai 201109,China)
出处
《沈阳航空航天大学学报》
2019年第6期14-21,共8页
Journal of Shenyang Aerospace University
关键词
低雷诺数
速度
流场结构
分离
数值模拟
low Reynolds number
velocity
flow field structure
separation
numerical simulation
