基于混合网格的低声爆反设计方法研究  

Low boom inverse design method based on hybrid grid

作　　者：冯晓强[1] 宋笔锋[1] 李占科[1] 

机构地区：[1]西北工业大学航空学院,西安710072

出　　处：《计算力学学报》2013年第5期717-722,共6页Chinese Journal of Computational Mechanics

基　　金：西北工业大学博士论文创新基金(CX201232)资助项目

摘　　要：低声爆设计方法已成为新一代军民用超声速飞机研制过程中必须解决的关键难题之一。针对传统SGD低声爆外形反设计方法无法对声爆近场非线性效应进行描述和分析的缺点,提出了利用CFD方法求解得到的声爆近场压力分布代替F函数进行低声爆反设计的方法。声爆近场预测采用点-点对接的结构/非结构混合网格,充分利用非结构网格对复杂外形适应性强和结构化网格计算效率高的优点。结果分析表明,基于改进后的低声爆反设计方法得到的方案在声爆超压以及感觉噪声级等方面都比基于原始SGD方法得到的方案有较大改善。Low sonic boom design method has become one key technology of next generation of supersonic aircraft. The original SGD method can＇t evaluate the nonlinear effect of sonic boom in near field. The near field pressure distribution is used in inverse design to replace the F function. Near field prediction of sonic boom is based on point to point structured/unstructured hybrid grid, avoiding the difficulty of generating structure grid on complex aircraft configuration and improving the analysis efficiency. The results demonstrate that the low boom configuration based on the new inverse design method has lower sonic boom overpressure and perceived level of loudness than low boom configuration based on original SGD method.

关 键 词：超声速客机 激波 声爆 反设计方法 结构 非结构混合网格 

分 类 号：V221.3[航空宇航科学与技术—飞行器设计]