李仁凤, 乐贵高, 马大为, 陈帅. 扇翼飞行器气动特性优化设计[J]. 空气动力学学报, 2017, 35(6): 879-882, 892. DOI: 10.7638/kqdlxxb-2015.0173
引用本文: 李仁凤, 乐贵高, 马大为, 陈帅. 扇翼飞行器气动特性优化设计[J]. 空气动力学学报, 2017, 35(6): 879-882, 892. DOI: 10.7638/kqdlxxb-2015.0173
LI Renfeng, LE Guigao, MA Dawei, CHEN Shuai. Optimization design for aerodynamic performance of fan-wing aircraft[J]. ACTA AERODYNAMICA SINICA, 2017, 35(6): 879-882, 892. DOI: 10.7638/kqdlxxb-2015.0173
Citation: LI Renfeng, LE Guigao, MA Dawei, CHEN Shuai. Optimization design for aerodynamic performance of fan-wing aircraft[J]. ACTA AERODYNAMICA SINICA, 2017, 35(6): 879-882, 892. DOI: 10.7638/kqdlxxb-2015.0173

扇翼飞行器气动特性优化设计

Optimization design for aerodynamic performance of fan-wing aircraft

  • 摘要: 采用多目标优化和数值模拟结合的方法对扇翼飞行器气动特性进行了优化研究。CFD计算结果与文献结果对比,验证了数值方法的可靠性。计算得到多结构参数影响下扇翼飞行器高升力、低阻力的优化结构参数和主要影响因素。研究结果表明,建立的近似数学模型和优化结果精度较高,满足工程需要。优化后,扇翼飞行器的升力和推力较大,飞行器气动特性得到显著改善。

     

    Abstract: Multi-point/objective design optimization technique combined with numerical simulation methods was adopted to study the optimization design for aerodynamic performance of fan-wing aircrafts. By comparing the present computational fluid dynamics (CFD) results with corresponding literature data, it proves that the numerical methods are reliable. The optimized lift and drag forces of a fan-wing aircraft were obtained for different structure parameters, and the factors with major influence on the optimization were also given. The results show that the approximate mathematical model is reliable. It can be adopted for engineering problems. Due to the optimization, the lift and thrust values of the fan-wing aircraft increases, and the aerodynamic performance dramatically improves.

     

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