The invention relates to an aircraft support member aerodynamic profile. The invention relates to a main rotor blade profile, and more particularly, to a blade root profile. The aircraft support member HYB-2 aerodynamic profile contains a profile of upper and lower areas. The profile thickness can be measured according to the ratio of the maximum thickness of the section to the chord percentage, and the profile thickness is 10-25%. The aircraft support member aerodynamic profile includes an upper surface and a lower surface, a profile formed by a convex curve and an intersection of the convex curve with specified coordinates relative to a profile chord. The convex curve coordinates are measured from the center line of the profile, and the upper coordinates are added and the lower coordinates are subtracted at the moment. The aerodynamic profile of the support member designed according to the nature of the present invention has acceptable load bearing capacity and profile resistance, as well as improved mass (compared to the known profile of the root section of the main rotor blade). In addition, the HH < 2 > section has a more stable focus position when the Mach number is changed, and the blade obtains higher maximum thrust when the wind resistance strength is increased.

    本发明涉及飞行器支承构件空气动力剖面。本发明涉及主旋翼桨叶剖面,更具体地来说,就涉及桨叶根部的剖面。飞行器支承构件НЦВ‑2空气动力剖面含有上与下面积的轮廓。以剖面最大厚度与弦百分之的比值,便可测定轮廓厚度,为10至25%。飞行器支承构件空气动力剖面包含上面及下面,由凸曲线及其与相对于轮廓弦的指定坐标的交点形成的轮廓。凸曲线坐标是从剖面的中线测量的,此时要加上上面坐标,而减去下面坐标。根据本发明本质设计的支承构件空气动力剖面具有可接受的承载能力及剖面阻力,以及提高到的质量(与已知的主旋翼桨叶根部截面的剖面相比)。此外,该НЦВ‑2剖面在改变马赫数时具有更稳定的焦点位置,还有增加的抗风强度时,让桨叶获得更高最大推力。


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    Title :

    Aircraft support member aerodynamic profile


    Additional title:

    飞行器支承构件空气动力剖面


    Contributors:

    Publication date :

    2022-11-15


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



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