关于高超声速绕流问题的激波层方法
On Shock Layer Method for the Hypersonic Flow Problems
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摘要: 切尔诺依(ГГ.Черный)的高超声速绕流激波层的级数解法,不适用于(γ-1)/(γ+1)<<2/(γ十1)M2sin2β(γ=cp/cv为绝热指数,M为马赫数,β为激波倾角)的情形。本文只假定在激波邻近存在激波层,在此薄层内,气体密度很大,但不排除(γ-1)/(γ+1)<<2/(γ+1)M2sin2β的情形。Abstract: Chernyi's series method is not proper for the case that(γ-l)/(γ+l)<<2/(γ+1)(M2sin2β)(γ=cp/cv-adiabatic index number, M-Much number, shock incidence). In this paper, we only suppose that in the neighbour of the shock, there exists a shock layer in which the density of the gas is very big, but we do not remove the case that (γ-1)/(γ+1)<<2/(γ+1)(M2sin2β).
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[1] Черный Г.Г.,Теченuя Газа с Болъuоu Сберхзбуковоu Скоросmыо,(1959)125-139. [2] Швец М.Е.,О Приближенном решении некоторых залач гидродинамики пограничного слоя,ПММ.,3(1949),257-266. [3] Аржаников Н.С.,Г.С.Садекова,Азробuнамuка Болошuх Скоросmеu(1965).373-380. [4] 复旦大学数学系编,《流体力学》(1860), 521. -
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