摘要
为使三维机翼尾涡卷曲更加真实,在计算诱导速度时引入衰减函数和有限半径涡核分别体现流体黏性作用下尾涡强度的衰减和尾涡扩散.应用面元法解析式计算奇点的诱导速度,在偶极附近区域用涡环代替偶极,利用尾涡面上的运动学条件来确定尾涡面的卷曲形状.数值模拟结果表明:涡核半径参数有一最佳值;考虑尾涡衰减可使卷曲更接近实验结果;采用曲线拟合方法确定衰减函数是可行的.
To make wake rollup more actual, the attenuation function and limited radius vortex core were introduced to express the attenuating and diffusing impact of fluid viscosity respectively on vortex sheet when the induced velocity was calculated. The induced velocity of singular points was calculated by analytic formula of surface panel method. The dipole was replaced by vortex ring in the near field of the dipole, and the geometry of vortex sheet rollup was determined by the kinematic condition on vortex sheet. Numerical simulation results show that there is an optimum value of limited radius vortex core, the attenuation function can make rollup closer to experimental results, and curve fitting method for obtaining the attenuation function is feasible.
出处
《大连海事大学学报》
CAS
CSCD
北大核心
2009年第2期136-140,共5页
Journal of Dalian Maritime University
基金
水下智能机器人技术国防科技重点实验室开放课题研究基金资助项目(2007015)
关键词
机翼
尾涡卷曲
衰减函数
有限涡核
foil
vortex sheet rollup
attenuation function
limited radius vortex core
