模拟细长翼分离涡的多涡线法改进  

AN IMPROVED MULTIPLE LINE-VORTEX METHOD FOR SIMULATION OF SEPARATED VORTICES OF SLENDER WINGS

作　　者：郭文海[1] 忻鼎定[2] 庄逢甘[2] 

机构地区：[1]中国科学院力学所计算站,北京100080 [2]北京航空航天大学流体所,北京100083

出　　处：《航空学报》1992年第1期A087-A090,共4页Acta Aeronautica et Astronautica Sinica

摘　　要：针对多涡线模型计算细长翼前缘分离涡时的不足,提出了改进措施。计算中使散乱的自由涡线合并成涡核,自由涡线、输送涡线和涡核满足不受力条件;物面上满足不穿透条件及边缘Kutta条件。选择初值迭代求解自由涡线、涡核的强度和位置。计算结果表明,本文方法收敛性好,计算时间短,能较准确地算出细长翼气动力和表面压力分布,对平面形状复杂的细长翼也能给出满意的结果。A improved vortical lines method has been made to simulate the separated vortices slender wings. The idea of the improved method is to merge free vortical lines into cores so that chaotic motion of vortical lines can be avoided. On the other hand, to form cores is also a good way to simulate the actual vortical movement. The strength and position of vortical cores and lines can iteratively be got by satisfying boundary conditions. Numerical results show that convergent quality of the method is good. Results are basically consistent with experimental results. Conclusively, the vortical flow of slender wings can be satisfactorily simulated by the paper's method.

关 键 词：细长机翼 分离流 数值计算 机翼 

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]