摘要
文章阐述了基于亚音速偶极子网格法的连续突风响应改进算法。采用四次多项式来近似增量核函数分子,放宽了非定常气动力计算中对气动网格展弦比的限制。以弹性机翼结构为例,探讨了气动网格单元展弦比和网格数对连续突风响应计算结果的影响。对比经典算法、改进算法计算结果,表明改进算法可行有效。该算法减少了高频气动力计算中所需的展向网格数目,可以节约计算时间或存储空间并提高计算精度,对突风控制与减缓研究有一定的指导作用。
Aim. The introduction of the full paper reviews some relevant papers in the open literature, points out what we believe to be their shortcomings, and then proposes what we believe to be an improved algorithm mentioned in the title. Sections 1,2, and 3 explain our improved algorithm; their core consists of： ＂The increment of kernel function molecules is matched by quartic polynomial, which relaxes the restriction of the span-chord ratio in the cal- culation of unsteady aerodynamic force. It investigates the effect to the computation of an elastic wing gust response by the span-chord ratio and the number of aerodynamic grids. ＂ The response results, obtained with classical algo- rithm and our improved one respectively, are presented in Figs. 4 through 9 and Tables 2 and 3. These results and their analysis show preliminarily that our improved algorithm is indeed feasible and effective.＂ This algorithm reduces the number of grids used in the high frequency aerodynamic force computation so that the calculating time and stored space are reduced; in addition, the accuracy is higher. It benefits the investigation of gust control and alleviation.
出处
《西北工业大学学报》
EI
CAS
CSCD
北大核心
2011年第6期909-914,共6页
Journal of Northwestern Polytechnical University
关键词
弹性机翼
突风响应
非定常气动力
偶极子网格法
aircraft, algorithms, calculations, computational geometry, control, functions, polynomials, subsonicaerodynamics, unsteady flow, wings
doublet-lattice method, gust response
