Numerical Simulation of Rotor Flow Field Based on Overset Grids and Several Spatial and Temporal Discretization Schemes

• Published in: Chinese journal of aeronautics Vol. 25; no. 2; pp. 155 - 163
• Main Authors: ZHAO, Ming, CAO, Yihua
• Format: Journal Article
• Language: English
• Published: Elsevier Ltd 01.04.2012
• Subjects: computational fluid dynamics; finite volume method; helicopters; Navier-Stokes方程; overset grids; rotors; Runge-Kutta法; 数值模拟; 时空; 流场计算; 空间离散; 转子; 通量向量分裂格式; rotors; helicopters; finite volume method; computational fluid dynamics; overset grids
• ISSN: 1000-9361
• DOI: 10.1016/S1000-9361(11)60374-9

A numerical method based on solutions of Euler/Navier-Stokes （N-S） equations is developed for calculating the flow field over a rotor in hover. Jameson central scheme, van Leer flux-vector splitting scheme, advection upwind splitting method （AUSM） scheme, upwind AUSM/van Leer scheme, AUSM＋ scheme and AUSMDV scheme are implemented for spatial discretization, and van Albada limiter is also applied. For temporal discretization, both explicit Runge-Kutta method and implicit lower-upper symmetric Gauss-Seidel （LU-SGS） method are attempted. Simultaneously, overset grid technique is adopted. In detail, hole-map method is utilized to identify intergrid boundary points （IGBPs）. Furthermore, aimed at identification issue of donor elements, inverse-map method is implemented. Eventually, blade surface pressure distributions derived from numerical simulation are validated compared with experimental data, showing that all the schemes mentioned above have the capability to predict the rotor flow field accurately. At the same time, vorticity contours are illustrated for analysis, and other characteristics are also analyzed.