Receptivity of the transonic boundary layer to acoustic noise

跨音速边界层对声学噪声的感受性

• 批准号: 1832038
• 金额: --
• 依托单位: Imperial College London
• 依托单位国家: 英国
• 项目类别: Studentship
• 财政年份: 2016
• 资助国家: 英国
• 起止时间: 2016 至 无数据
• 项目状态: 已结题
• 来源: https://gtr.ukri.org/projects?ref=studentship-1832038
• 关键词: Receptivity; transonic; boundary; layer; acoustic

Currently a major priority in passenger aircraft design is to delay laminar-turbulent transition in the boundary layer on aircraft wings. It has been identified that acoustic noise, free-stream turbulence and wall roughness are responsible for the laminar-turbulent transition which starts with the receptivity of the boundary layer to external perturbations. This project will focus on the receptivity in transonic speed regimes. Both the generation of the Tollmien-Schlichting waves and of the Cross-Flow vortices will be studied. For this purpose the asymptotic solutions of the Navier-Stokes equations will be constructed assuming that the Reynolds number is large. Based on these solutions the means to control the laminar-turbulent transition by suppressing the receptivity process will be developed.

目前客机设计的一个主要优先事项是延迟飞机机翼边界层的层流-湍流转变。人们已经确定，声学噪声、自由流湍流和壁粗糙度是层流-湍流转变的原因，该转变始于边界层对外部扰动的接受能力。该项目将重点关注跨音速速度状态下的接收能力。将研究 Tollmien-Schlichting 波和错流涡流的产生。为此，将在假设雷诺数很大的情况下构造纳维-斯托克斯方程的渐近解。基于这些解决方案，将开发通过抑制接受过程来控制层流-湍流转变的方法。