The present invention provides a variable wing leading edge camber. The disclosed method reduces a wave drag on an airfoil traveling at a speed. At least a portion of the airfoil is configured to be selectively moveable between a first position and a second position. The first position is a neutral position, and the second position generates a shock wave near to the leading edge of the airfoil. The method includes the steps of maintaining the airfoil in the first position when the speed is less than a first limit and moving the airfoil to the second position when the speed is greater than a first limit.

    可变机翼前缘弯度。所公开的方法减小了在一定速度下航行的翼型上的波阻。翼型的至少一部分被构造成能够选择性地在第一位置与第二位置之间移动。第一位置是中性位置,并且第二位置在翼型的前缘附近生成冲击波。该方法包括以下步骤:当速度小于第一极限时,将翼型维持在第一位置;以及当速度大于第一极限时,将翼型移动到第二位置。


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    Title :

    Variable wing leading edge camber


    Additional title:

    可变机翼前缘弯度


    Contributors:

    Publication date :

    2021-06-29


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



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