跨声速三角翼旋涡破裂过程的数值模拟  

Numerical Simulation of the Vortex Breakdown Transition over a Delta Wing in Transonic Flow

作　　者：庞勇[1] 张树海[1] 张涵信[1] 

机构地区：[1]中国空气动力研究与发展中心

出　　处：《空气动力学学报》1999年第2期195-202,共8页Acta Aerodynamica Sinica

基　　金：国家自然科学基金

摘　　要：本文利用张涵信提出的时、空二阶精度的隐式混合通量分裂的ＮＮＤ格式，通过求解非定常ＮＳ方程模拟了马赫数Ｍ为０．８、迎角α为２１．８°时某外形三角翼背风区旋涡破裂的发展、演变过程，并对旋涡区域的截面流态和涡轴上奇点附近的空间流动特征进行了分析。The procedure of the vortex breakdown transition at high angle of attack over a delta wing is investigated numerically by solving the unsteady full Navier Stokes equation.An implicit,hybrid flux splitting NND scheme having a second order accurate in both time and space is used here.The results are presented for a 63° sweep,sharp leading edge delta wing at Mach number of 0.8,angle of attack of 21.8° and Reynolds number of 1.0×10 6.Vortex breakdown is found,and the procedure of its development and transition can be divided into three regions.They are a region of the bubble type breakdown first,a region of a spiral type then and a region of the bubble type finally.The cross sectional flow characteristics on the cross section passing though the vortex cell and the spatial flow characteristics near the singular points along the vortex axis are analyzed.Topological aspects of the bubble type vortex breakdown flowfield are also presented and discussed.

关 键 词：NND格式 跨声速流 旋涡破裂 数值模拟 三角翼 

分 类 号：V211.41[航空宇航科学与技术—航空宇航推进理论与工程] O354.2[理学—流体力学]