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改善下一代民航机空气动力效率的技术已成为航空科学中重要课题之一。高气动力效率要求在超临界Mach数下飞行,并要避免激波的出现或使激波变得足够弱。跨音速设计方法可以实现无激波或接近无激波的流动。解决跨音速设计问题往往是和发展可靠的流动分析方法相联系的。“椭圆连续”或“虚拟气体”方法是一种有效的设计方法。此方法及其应用于翼型和机翼的设计已概述于文献[1,2]。这种概念首先由H.Sobieczky给以说明:用一种数值计算方法来求解绕基本翼流动的一组虚拟气体的方程组,这些方
Technology to improve the aerodynamic efficiency of the next generation of civil aircraft has become one of the major topics in aviation science. High aerodynamic efficiency requires flying under supercritical Mach numbers and avoiding the appearance of shocks or making the shocks weak enough. Transonic design approaches achieve either no shock or near-shock-free flow. Solving transonic design problems is often linked to developing robust flow analysis methods. The “elliptical continuous” or “virtual gas” approach is an effective design method. This method and its application to the design of airfoils and wings have been outlined in the literature [1,2]. This concept was first given by H. Sobieczky to illustrate that a numerical method is used to find a system of equations for a set of virtual gases flowing around a basic wing,