摘要
提出了一种求解带副翼偏转三维机翼绕流的Ｎ－Ｓ方程计算方法。采用对接分区网格与分区求解算法的结合，有效地求解绕此外形的复杂流动。提出了一种满足通量守恒的内边界耦合条件。数值方法中选用ｖａｎＬｅｅｒ分裂格式离散无粘通量项，并构造了一种Ｌｉｍｉｔｅｒ函数以保证ＴＶＤ性质，采用中心差分格式来离散粘性通量项。数值算例表明该方法是求解带操纵面偏转的机翼绕流的有效方法。
An N S method for solving the flow around a wing with deflection of control surface (aileron) is presented. Using the combination of patched grid and domain decomposition techniques, the complex flow around this kind of configuration is effectively solved. An internal coupling condition satisfying the conservation of flux is given. In the computation, van Leer′s scheme is used to discretize the inviscid flux terms and a new limiter function is constructed to realize TVD character. The viscous flux terms are discretized by using a central difference scheme. Numerical results show that the present method is effective for solving the flow around a wing with control surface deflection.
出处
《航空学报》
EI
CAS
CSCD
北大核心
1999年第3期197-200,共4页
Acta Aeronautica et Astronautica Sinica
关键词
N-S方程
分区算法
机翼
副翼
三维
绕流
N S equations
domain decomposition method
flow with control surface deflection
