摘要
应用NURBS技术构造超声速叶型,采用两个控制参数调整叶栅前缘椭圆弧的几何形状,来探索不同的前缘构型对超声速叶型气动性能的影响效应;通过对比分析调整每个参数所得的一系列叶栅的流场计算结果,发现椭圆弧的形状控制因子对超声速叶栅的前缘激波和气流流动状况具有一定的改善效果,同时在保证叶栅气动弦长基本不变的情况下,存在某个椭圆弧形状控制因子和方向控制因子的匹配能够使叶栅的气动性能达到最佳.
NURBS method was applied to reshape some supersonic airfoils, and two controlling parameters were used to adjust the geometric shape of supersonic airfoil＇s leading edge, these methods were adopted to investigate the supersonic airfoil＇s aero-dynamic performance influence effect with different leading edge geometric shape; The contrastive analysis results, which were obtained from a series of airfoil＇s flow field structure with changing each controlling parameter, shown ellipse shape controlling factor not only could weaken the shock wave intensity near the leading edge region of airfoil but also could improve the flow field structure. At the same time, this paper demonstrated that the matching between some ellipse shape controlling factor and some ellipse direction controlling factor could make the responding supersonic airfoil＇s aero-dynamic performance reach to the best while its chord keeping no change.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2007年第4期660-665,共6页
Journal of Aerospace Power
关键词
航空
航天推进系统
NURBS
椭圆圆弧
超声速叶片
气动性能
效应
aerospace propulsion system
NURBS
ellipse edge arc
supersonic airfoil
aero-dynamic performance effect
