The invention belongs to the technical field of aviation, and particularly relates to an airfoil profile for an aircraft based on logarithmic spiral lines. According to the airfoil profile, the lift-drag ratio of the airfoil profile in the flight state of an aircraft can be increased, the surface stress of the airfoil profile in the cruise state is more uniform, and a new thought is provided for subsequent design optimization of aircraft wings. The aircraft airfoil comprises the following parts: taking a front edge end point of an airfoil as a logarithmic helix starting point, taking a rear edge end point as a logarithmic helix ending point, and carrying out constraint nonlinear fitting to obtain the logarithmic helix airfoil.

    本发明属于航空技术领域,尤其涉及一种基于对数螺旋线的飞机用翼型。该翼型可以提升飞机在飞行状态下翼型的升阻比,且翼型在巡航状态下表面受力更加均匀,为后续飞机机翼的设计优化提供了新思路。包括:以翼型的前缘端点为对数螺旋线起点,以后缘端点为对数螺旋线终点,进行约束非线性拟合得到对数螺旋线翼型。


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    Title :

    aircraft airfoil based on logarithmic spiral


    Additional title:

    一种基于对数螺旋线的飞机用翼型


    Contributors:
    SONG HUA (author) / LIU XIAOLONG (author) / WANG YANG (author) / YANG JIAN (author) / GAO MINGXIN (author) / LIAN FABO (author) / FU LIHUA (author)

    Publication date :

    2022-02-08


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    G06F ELECTRIC DIGITAL DATA PROCESSING , Elektrische digitale Datenverarbeitung / B64C AEROPLANES , Flugzeuge



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