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本文研究了对较小展弦比的三角形机翼采取适当的扭转和弯曲,推迟气流前缘分离,使之在设计状态下实现最小诱导阻力的问题。文中理论部分,应用亚音速锥型流理论,提出了一种设计最小诱阻三角形扭曲机翼的解析方法,并对两个不同设计状态的算例进行了数值计算。实验部分,对带有三角形前缘扭曲机翼(设计状态:M_∞=0,C_L=0.20)和三角形平面机翼的两种翼身组合体,进行了纵向三分力试验,作了理论和实验结果的比较分析。结果表明:按本文方法设计的前缘扭曲机翼,其翼身组合体在设计状态下,实现了理论预期的最小诱导阻力值,组合体的升阻特性有了显著的改善。
In this paper, the problem of minimizing induced drag in the designed state is studied by adopting appropriate torsion and bending for the triangular wing with smaller aspect ratio and delaying the separation of the leading edge of the airflow. In the theoretical part of this paper, a subsonic cone flow theory is used to design an analytical method for designing a minimum-torsion triangular torsion wing. Numerical examples are given for two different design states. In the experimental part, a longitudinal three-component test was carried out on two wing-body assemblies with triangular leading edge twisted wings (design state: M_∞ = 0, C_L = 0.20) and triangular planar wings. Comparative Analysis of Experimental Results. The results show that the front wing twisted wing designed by this method achieves the theoretically expected minimum induced resistance under the designed condition, and the lift resistance characteristics of the composite body have been significantly improved.