Development of Preliminary Design Oriented CFD Solver and its Application to Environment Friendly Aircraft Design

在这项研究中，我们开发了一个面向概念设计的计算流体动力学代码，是快速和强大的。这两个因素在飞机的概念设计阶段尤为重要。为了处理任意复杂的几何形状，使用具有自适应网格细化的笛卡尔网格。利用该网格，用程序求解了可压缩Navier-Stokes方程。我们在壁面边界条件处理（浸没边界法）、物体受力计算方法、与湍流模型的耦合、高阶格式的发展等方面进行了不懈的努力。通过这些改进，该程序可用于飞机设计中出现的许多流动条件，如起飞和着陆时的低速流动、超音速巡航时的波阻估算等。此外，该程序还将扩展到非定常气动声学流场模拟的应用中。

In this study, we developed a conceptual-design-oriented computational fluid dynamics code that is fast and robust. These two factors are required especially during the conceptual design phase of an aircraft. In order to handle an arbitrary complex geometry, Cartesian grid with adaptive mesh refinement is used. Using this grid, compressible Navier-Stokes equations are solve by the program. We have worked constantly on many topics: wall boundary condition treatment (Immersed boundary method), calculation method for force acing on a body, coupling with turbulence model, the development of high-order scheme. Through these development, the code now can be applied to many flow conditions which appears during aircraft designing, such as low-speed flow during take-off and landing, wave drag estimation during super-sonic cruise. Additionally, the code is being extended to the application of unsteady aeroacoustic flow simulation.