Abstract Current design requirements are shaping advanced and efficient supersonic or hypersonic aircraft concepts, capable of flying between distant parts of the globe within hours, and making affordable and safe access-to-space transportation. To achieve this challenge, reliable design tools, like Computational Fluid Dynamics, are strongly integrated in multidisciplinary design procedures. In this framework, the present paper deals with the importance and capabilities of Computational Fluid Dynamics investigations, especially those involved in vehicle aerodynamic and aerothermodynamic appraisal, to support and feed the design of high-speed aircraft. At first the Computational Fluid Dynamics support in various phases of design is addressed. Furthermore, an overall vision on methodologies used in a high speed flow computation is also given, addressing advantages and drawbacks of classical methodologies versus modern hybrid RANS methods ones. Then, a brief overview on either numerical schemes and tools, routinely adopted in an hypersonic simulation, is presented with reference to the multi-scale accuracy required by high supersonic/hypersonic flow regime. Finally, to provide a complete template for future numerical experiments, several Computational Fluid Dynamics activities, performed for a number of high-speed aircraft in different flow regimes, ranging from subsonic up to hypersonic speed, are reported and discussed. Computational methodology, domain discretization, and the support to design activity are provided for the CIRA USV1 and USV3, ESA-IXV, HEXAFLY-INT, a space launcher, and a Mars entry capsule. These examples show that Computational Fluid Dynamics can no longer be considered only an analysis tool, but it allows great advantages in all design stages, from conceptual up to detailed design level.

中文翻译：

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下一代高速飞机的 CFD 设计能力

摘要 当前的设计要求正在塑造先进和高效的超音速或高超音速飞机概念，能够在数小时内在地球遥远的地方之间飞行，并提供价格合理且安全的太空运输。为了应对这一挑战，可靠的设计工具（如计算流体动力学）与多学科设计程序紧密集成。在这个框架中，本文讨论了计算流体动力学研究的重要性和能力，尤其是那些涉及车辆空气动力学和空气热力学评估的研究，以支持和支持高速飞机的设计。首先解决了在设计的各个阶段的计算流体动力学支持。此外，还给出了高速流计算中使用的方法的总体愿景，解决经典方法与现代混合 RANS 方法的优缺点。然后，参考高超声速/高超声速流态所需的多尺度精度，简要概述了高超声速模拟中常规采用的数值方案和工具。最后，为了为未来的数值实验提供一个完整的模板，报告和讨论了针对不同流态（从亚音速到高超音速）的许多高速飞机执行的几种计算流体动力学活动。为 CIRA USV1 和 USV3、ESA-IXV、HEXAFLY-INT、太空发射器和火星进入舱提供计算方法、域离散化和设计活动支持。