The invention relates to near space aerocrafts, in particular to a method for designing a double-air-inlet hypersonic-velocity wave-rider aircraft. Aerodynamic features are firstly designated, and then a design scheme meeting the features is reversely derived. A certain three-dimensional shock wave curved surface in a complex shape is designated, and the change rule of the transverse curvature center of the three-dimensional shock wave curved surface is obtained. A series of basic flow fields needed in wave rider design are reversely derived. Flow line tracking with different curvature centers and different longitudinal positions is carried out in the basic flow field at each circumferential position. Finally, a wave rider device capable of generating the designated complex three-dimensional shock wave curved surface is obtained, and the design scheme of the double-air-inlet hypersonic-velocity wave-rider aircraft is completed. Integration of the aircraft and air inlets is achieved, meanwhile, double-air-inlet design is achieved, and a solving method is provided for the design of a double-engine hypersonic-velocity aircraft.


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    Titel :

    Method for designing double-air-inlet hypersonic-velocity wave-rider aircraft


    Beteiligte:
    LI YIQING (Autor:in) / YOU YANCHENG (Autor:in) / TENG JIAN (Autor:in) / PAN CHENGJIAN (Autor:in)

    Erscheinungsdatum :

    2015-12-30


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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