摘要
描述了求解直升机旋翼悬停流场的数值方法。利用悬停流场的准定常特性，采用有限体积空间离散和龙格库塔时间步进格式，在桨叶固连旋转坐标系下直接求解以相对物理参数为变量的三维无粘可压欧拉方程，没有附加任何尾迹模型，其中，应用了多项加快收敛技术。计算了二叶模型旋翼在亚、超音速的流动，并与相应的国外实验数据作了对比，吻合良好。表明应用欧拉方程能够模拟多叶旋翼的悬停流场。
Wake model, usually required for calculating flowfield for lifting rotor in hover, is not quite convenient owing to its semi - empirical nature.We employ a blade - attached coordinate system with the obvious advantage of treating the flowfield as a steady one. Then we recast the inviscid and compressible Eu1er equations in absolute flow variables; such recasting makes the farfield of absolute flow uniform and allows the more accurate calculation of the fluxes. The rotational flux due to the rotating frame can be calculated exactly for each cell fftce using the Stokes theorem. For the solution of Euler equations we employ a finite - volume method and the 5 - stage Runge - Kutta scheme. The technique of local time stepping, rothalpy damping and implicit residual smoothing are used to increase the convergence rate. The steady flow around the rotor blade is calculated; moreover the pressure distributions and the position of tip vortex are determined for two - bladed rotor. The calculated results correlate fairly well with experimental data.
出处
《西北工业大学学报》
EI
CAS
CSCD
北大核心
1998年第4期594-598,共5页
Journal of Northwestern Polytechnical University
