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采用DISC方法耦合N-S方程求解程序研究了无尾布局翼型的设计。通过NLF1015,RAE2822翼型的反设计表明,该方法可用于亚、跨声速翼型设计,具有简单、计算量小的优点。完成了翼型改进和新翼型设计,对某BWB飞机内翼段翼型进行了改进设计,采用人工干预对现有翼型压力分布进行局部修正,达到快速削弱激波、改善翼型气动性能的目的;针对小展弦比翼身融合布局内翼段新翼型设计,采用基于多目标多约束压力分布优化的设计思想,得到满足气动和几何约束的目标压力分布。设计结果表明,数值优化目标压力分布方法较易满足总体与气动的设计目标和约束。
DISC method coupled to N-S equation solver was used to study the design of a tailless layout airfoil. By NLF1015, RAE2822 airfoil inverse design shows that the method can be used for sub-transonic airfoil design, with the advantages of small amount of calculation. The airfoil improvement and new airfoil design are completed. The airfoil shape of the inner wing of a BWB aircraft is improved. The manual intervention is used to locally modify the existing airfoil pressure distribution to rapidly weaken the shock wave and improve the airfoil aerodynamic performance Aiming at the new wing design of inner wing section with small aspect ratio fuselage fusion layout, aiming at the target pressure distribution satisfying the aerodynamic and geometrical constraints, the design idea based on multi-objective and multi-constraint pressure distribution optimization is adopted. The design results show that numerical optimization of target pressure distribution method can easily meet the overall and aerodynamic design goals and constraints.