摘要
以大型运输机机翼为研究对象,针对其机翼高低速气动外形设计目标,采用改进的Takanashi正反迭代、余量修正方法,进行超临界翼型的大型运输机机翼气动外形反设计。采用优化方法进行三维机翼低速增升装置的优化设计,通过将气动外形优化设计方法与反设计方法相结合以及分布式并行计算等手段来提高设计效率。结果表明,该设计方法是合理可行的。
The aerodynamics design methods of wing for large transport aircraft are researched and developed in this paper.An improved inverse design method based on Takanashi＇s iterative residual correction principle is developed to design supercritical wing for large transport aircraft,meanwhile a optimization method is developed to design low speed high-lift configuration of wing,which combines the optimization method with the distributed parallel computing in LAN（local-area-network） to enhance the efficiency.Design examples show that the design method is feasible and provide practical tool for the aerodynamics design of wing for large transport aircraft.
出处
《飞行力学》
CSCD
北大核心
2009年第2期28-30,41,共4页
Flight Dynamics
关键词
大型运输机
反设计
机翼
增升装置
遗传算法
large transport aircraft
inverse design
supercritical wing
high-lift configuration
genetic algorithm
