CFD design capabilities for next generation high-speed aircraft

摘要

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.