摘要
本文以Ｎ－Ｓ方程和Ｈａｌｌ涡核模型假设为基础，导出了描述湍流的涡核运动方程。利用差分计算方法，对三角翼前缘分离涡运动及其破碎特性进行了数值求解，分析了涡核流场的结构和各物理量的变化特性，反映了三角翼前缘分离涡运动及其破碎特性的实质，说明了湍流涡核方程能更有效地模拟三角翼前缘分离涡运动和准确地确定涡核破碎位置，并得出了攻角和雷诺数对破碎位置的影响，计算结果与实验数据十分吻合。
In this paper, the motion equations of turbulent vortex- core based on N-S equations and Hall’s vortex-core model hypothesis bave been drived.The motion and breakdown of leading-edge vortices are solved by difference method and the mechanism of the vortex-core flow field are analyzed.The results reflect the essence of the motion and break down of leading-edge separated vortices on delta wing,It is showed that the turbulent vortex-core equatins are more efficient to model the motion of leading-edge separated vortices and determine the bursting-location of leading-edge separated vortices.This metbod can obtain the effects of angle of attack and Reynolds number on the vortex-breakdown location. The calculated results agree well with the experimental data.
出处
《空气动力学学报》
CSCD
北大核心
1995年第3期323-328,共6页
Acta Aerodynamica Sinica
关键词
前缘分离涡
涡破碎
三角翼
湍流
leading-edge separated vortices,vortex-breakdown,delta wing,turbulent flow.
