In order to reduce noise, the invention proposes an airfoil profile (30) for an aircraft (10), such as an unmanned aerial system (11). The airfoil profile (30) comprises: a leading edge portion (31) and a trailing edge portion (32), the leading edge portion and the trailing edge portion being spaced apart in a chord direction; an airfoil centroid (33); and an upper airfoil surface (40) and a lower airfoil surface (50). The airfoil surfaces (40, 50) are shaped such that the pressure center (Cp) of the lift is arranged at the same chord position as the airfoil centroid (33) or such that the pressure center of the lift is closer to the trailing edge portion (32) than the airfoil centroid (33) in the chord direction. As a result, a downdip momentum is generated that urges the leading edge portion (31) toward the lower angle of attack (AoA).

    为了减少噪音,本发明提出了一种用于飞行器(10)比如无人驾驶航空系统(11)的翼型轮廓(30)。该翼型轮廓(30)包括:前缘部分(31)和后缘部分(32),该前缘部分和该后缘部分沿着翼弦方向间隔开;翼型形心(33);以及上翼型表面(40)和下翼型表面(50)。翼型表面(40,50)定形状成使得升力的压力中心(Cp)与翼型形心(33)布置在相同的翼弦位置处或者使得升力的压力中心沿着翼弦方向比翼型形心(33)更靠近后缘部分(32)。由此,产生促使前缘部分(31)朝向较低的迎角(AoA)的下俯动量。


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    Title :

    Airfoil profile for aircraft and aerodynamic surface using said airfoil profile


    Additional title:

    用于飞行器的翼型轮廓和使用所述翼型轮廓的空气动力学表面


    Contributors:

    Publication date :

    2024-04-23


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64U / B64C AEROPLANES , Flugzeuge



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