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本文依据低速风洞实验、载荷分布计算和跨超音速面积律计算,分析了前掠翼布局飞机的气动特性,提出了提高前掠翼气动特性的措施,并用对称性原理解决面涡法和面积律计算方法对前掠翼布局的应用。实验研究和计算表明:前掠翼布局有较好的气动特性,翼梢小翼可提高前掠翼的升力及升阻比。近距耦合的鸭翼及前掠翼翼根填块对改善前掠翼根的气流分离有显著效果。前掠冀比后掠翼更接近最佳载荷分布。有鸭翼的前掠翼组合体的轴向截面分布较易接近最佳当量截面分布,因而可显著减小零升波阻。
Based on the low-speed wind tunnel experiment, the calculation of the load distribution and the calculation of the cross-supersonic area law, the aerodynamic characteristics of aircraft with forward-swept wing are analyzed and the measures to improve the aerodynamic characteristics of the forward-swept wing are proposed. The symmetry principle is used to solve the surface vortex method and area Application of Law Calculation Method to Forward Swept Wing Layout. Experimental studies and calculations show that the forward swept wing layout has good aerodynamic characteristics, and the winglet can improve the lift and drag ratio of the forward swept wing. Close-coupled canard wings and forward-grazing wing root blocks improve the airflow separation of the forward-swept-wing roots significantly. The preemphasis is closer to the optimal load distribution than the swept wing. The axial cross-section of the forward-swept wing combination with canard wings is closer to the optimal equivalent cross-section distribution, which can significantly reduce the zero-liter wave resistance.