3D Hypersonic Shock-Turbulent-Boundary-Layer Interactions

3D 高超声速激波-湍流-边界层相互作用

• 批准号: DP230101367
• 负责人: Prof Ananthanarayanan Veeraragavan
• 金额: $ 31.06万
• 依托单位: The University of Queensland
• 依托单位国家: 澳大利亚
• 项目类别: Discovery Projects
• 财政年份: 2023
• 资助国家: 澳大利亚
• 起止时间: 2023-07-03 至 2027-07-02
• 项目状态: 未结题
• 来源: https://dataportal.arc.gov.au/RGS/Web/Grants/DP230101367
• 关键词: 3D; Hypersonic; Shock; Turbulent; Boundary

Shock-wave turbulent-boundary-layer interactions occur on hypersonic flight vehicles and can lead to high heating and increased drag. This is a paramount design issue that needs addressing. We aim to understand and quantify fundamental phenomena occurring in such interactions using state-of-the-art instrumentation and wind-tunnel facilities. Surfaces will be heated to realistic flight temperatures to simulate accurately the flight environment and include effects not reproduced with cold models. The effects of 3D features of the interactions will lead to new understanding of how the flow develops through a combination of experiments and numerical simulations. Future designs of hypersonic flight vehicles will benefit from knowledge gained.

激波-湍流-边界层相互作用发生在高超声速飞行器上，并可能导致高热和阻力增加。这是一个需要解决的最重要的设计问题。我们的目标是使用最先进的仪器和风洞设施来理解和量化在这种相互作用中发生的基本现象。表面将被加热到真实的飞行温度，以准确地模拟飞行环境，并包括冷模型无法再现的效果。相互作用的三维特征的影响将通过实验和数值模拟相结合的方法，对流动是如何发展的有新的理解。未来高超声速飞行器的设计将受益于所获得的知识。