翼型-扰流片的分离气动特性计算  

Separated Aerodynamic Characteristic Calculation for Airfoil-Spoiler

作　　者：陈劲松[1] 孙少鹏[1] 

机构地区：[1]南京航空航天大学,江苏南京210016

出　　处：《空气动力学学报》1993年第4期423-427,共5页Acta Aerodynamica Sinica

摘　　要：本文介绍用涡面元法模拟带扰流片的翼型低速无粘分离绕流。在翼型和扰流片的面元上分布线性变化涡。在扰流片后的上下分离流线的面元上分布等强度的涡。上分离流线始自扰流片的梢部,下分离流线自翼型的后缘引出。分离气泡由两离散涡结尾。气泡内总压为常值,它与涡强大小一同求解。分离气泡的形状在迭代求解过程中确定。压强分布和升力系数的计算值与现存文献的数值结果和实验数据是一致的。A vortex panel method is presented to simulate low speed inviscid separated flow past an airfoil with a spoiler. Vorticity singularities are placed on the airfoil-spoiler surface, on the upper separated streamline from the spoiler tip and on the lower separated streamline from the airfoil trailing edge. The separated region is closed downstream by two discrete vortices.The flow inside the separated region is assumed to have uniform total head, which is solved together with the vorticity strength. The wake shape is iteratively obtained from an initial shape estimation. Predicted pressure distribution and lift coefficient are in agreement with numerical results and experimental data available in the literature.

关 键 词：翼型 无粘分离流 气动特性 计算 

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]