中文摘要：

建立了一个适用于前飞状态直升机单独旋翼、机身以及旋翼/机身组合体流场的数值计算方法及模型.在该方法中,使用非结构运动嵌套网格描述桨叶之间以及桨叶与机身之间的空间位置变化关系,控制方程采用惯性坐标系下的非定常Navier-Stokes(N-S)主控方程,空间方向上使用二阶迎风格式,时间方向上使用Lower-upper symmetric Gauss-Seidel(LU-SGS)格式.对于求解中遇到的旋翼/机身间距离过近所导致的贡献单元生成困难问题提出了一种新的解决方法.应用所建立的方法,分别对单独旋翼、机身及旋翼机身组合体的前飞绕流场进行了数值模拟与分析,计算结果与试验结果的对比表明本文建立的方法对直升机的前飞绕流场的计算和分析是很有效的.

英文摘要：

A numerical method has been developed to simulate the flowfield of the helicopter rotor,fuselage and the combination of them in forward flight.In this method,unstructured embedded grid technique was used to simulate the position transformation relationship between the rotor and its fuselage,the three-dimensional unsteady Navier-Stokes(N-S) equations were discretized by a second-order upwind finite-volume scheme and the lower-upper symmetric Gauss-Seidel(LU-SGS) scheme was employed in time-stepping.A new met...