The invention discloses a novel basic training aircraft airfoil which is applied to a wing tip position or a wing root position of a wing. When the airfoil is applied to the tip position of a wing, the lift coefficient of the airfoil is 0.2, the maximum relative thickness is 12%, the maximum thickness position is 38.3% C, the maximum camber is 1.80%, and the maximum camber position is 42.2% C; wherein C is the chord length, and all the parameters take the chord length of 1 as a reference; according to the technical requirements of the novel basic training aircraft, a special airfoil family is designed through an optimization design method, the airfoil performance is standard to foreign NACA63 series airfoils, the airfoil has the characteristics of high lift force, high lift-drag ratio and mild stall performance, the requirements of the novel basic training aircraft for the airfoil performance are met, and the airfoil is suitable for a new generation of basic training aircraft.

    本发明公开了一族新型基础教练机翼型,应用于机翼翼稍位置或翼根位置;当应用于机翼翼稍位置时:翼型的升力系数为0.2,最大相对厚度12%,最大厚度位置38.3%C,最大弯度1.80%,最大弯度位置42.2%C;其中,C为弦长,上述参数均以弦长为1为基准;本发明根据新型基础教练机的技术要求,通过优化设计方法设计出专门翼型族,翼型性能对标国外NACA63系列翼型,具有高升力、高升阻比和失速性能和缓的特点,满足新型基础教练机对翼型性能的要求,适应新一代基础教练机。


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    Titel :

    Novel basic training aircraft airfoil


    Weitere Titelangaben:

    一族新型基础教练机翼型


    Beteiligte:
    ZHANG WEI (Autor:in) / ZHANG KANGPING (Autor:in) / DENG LEI (Autor:in) / HAN BIN (Autor:in) / LEI YUWEI (Autor:in)

    Erscheinungsdatum :

    2022-06-10


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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