The invention discloses a hypersonic speed aircraft osculating curved surface waverider design method, and belongs to the technical field of aircraft design. According to the method, an osculating cone waverider design method is firstly improved, and the osculating cone waverider design method is subjected to continuation. On the basis of the Sobieczky three-dimensional flowing simplification, the process of transiting the osculating cone into the osculating wedge and then transiting the osculating wedge into the osculating inner cone is smooth; the transverse flowing is regarded to be weak; and the flowing mainly occurs in the osculating plane. Therefore a complicated cross section shockwave curve with any curvature can be divided into a concave curve section, a convex curve section and a transition section; a series of local osculating cone/wedge flows with identical shockwave strength are respectively used for approximation; and the obtained after-wave flow field has the second-order accuracy, and can be used for waverider design. The shockwave with any curvature cross section shape can be used for design; the waverider with the complicated plane shape is generated; and the waverider characteristic in the high-Mach range is improved.


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    Title :

    Hypersonic speed aircraft osculating curved surface waverider design method


    Contributors:
    JIANG CHONGWEN (author) / GAO ZHENXUN (author) / LI CHUNXUAN (author)

    Publication date :

    2015-12-23


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64F GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT , Boden- oder Flugzeugträgerdeckeinrichtungen besonders ausgebildet für die Verwendung in Verbindung mit Luftfahrzeugen



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