【摘 要】
：
In this talk,we study some mathematical aspects on supersonic flow past a delta wing.Here the wing is assumed to be infinite along its edges,so we need only to
【机 构】
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FudanUniversity,China
【出 处】
：
2014 workshop on nonlinear evolutionary partial differential
论文部分内容阅读
In this talk,we study some mathematical aspects on supersonic flow past a delta wing.Here the wing is assumed to be infinite along its edges,so we need only to seek self-similar solutions to this supersonic shock problem,which is formulated as a free boundary value problem of nonlinear mixed-type equation.In the case that the wing is of zero-thickness,the mixed-type equation then reduces to a degenerate elliptic equation,and thus an existence result can be established by using the framework of Chen-Feldman for regular shock reflection problem.Moreover,some differences between the regular shock reflection model and the general delta wing model are discussed.This talk is based on a joint work with my advisor Prof.Shuxing Chen.
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