压缩性对高超声速三维边界层转捩的影响研究

The three-dimensional hypersonic boundary layer transition is one of the most important and difficult problems of aerodynamics. It is restricted to research the effect of compressibility on the instability of hypersonic boundary layer by the limitation of precise measurement methods and data analysis methods. Based on the wind tunnel experiments, this proposal will research the parameterized definition of the different instability modes and the interaction between the different modes of disturbance during the three-dimensional transition process on the hypersonic cone, comprehensively using the multiple precise measurement methods combined with the data processing and analysis methods which can reveal the procession of boundary layer transition and the mechanism of instability. Then the type and characteristic of three-dimensional instability mechanism will be given for the hypersonic cone at different Mach numbers, including the effect rules of the compressibility on the hypersonic three-dimensional boundary layer transition. The aim of the proposal is to provide the theoretical basis for the precise prediction of hypersonic three-dimensional boundary layer transition, the effective transition control methods and the research of the mechanism of transition. Besides, it also can provide the technical support for the fine design of the hypersonic vehicles in the wide speed range.

高超声速三维边界层转捩问题是空气动力学研究领域的重点和难点之一，压缩性对高超声速边界层流动失稳的影响受到精细化的实验手段和数据处理与分析方法的制约。本项目采用风洞实验研究方法，综合运用多种高超声速三维边界层流场的精细化测量手段，结合能够揭示边界层转捩过程和失稳机制的实验数据处理和分析方法，对高超声速圆锥三维边界层转捩过程中的不同失稳模态参数化定义方法以及不同模态扰动的相互干扰进行研究，总结出不同马赫数下，高超声速圆锥三维边界层失稳机制的类型和特征，以及压缩性对高超声速三维边界层转捩的影响规律，为高超声速三维边界层转捩的精确预估、转捩有效控制方法及转捩物理机理研究提供理论基础，为宽速域高超声速飞行器的精细化设计提供技术支撑。

高超声速飞行器三维边界层转捩问题是空气动力学研究领域的重点和难点之一，高超声速边界层流动失稳机理研究受到精细化的实验手段和数据处理与分析方法的制约。本项目采用风洞实验研究方法，综合运用多种高超声速三维边界层流场的精细化测量手段和相应数据分析方法，对高超声速三维边界层转捩过程中的不同失稳模态辨识以及不同模态扰动的相互干扰进行研究。.首先，发展了基于红外热成像的高超声速边界层热流全局测量及转捩辨识方法，以及基于基于高频压力/热流信号的模态辨识分析方法，具备了高超声速边界层稳定性分析及转捩测量能力。然后，针对圆锥典型构型试验模型以及HyTRV高超声速飞行器转捩标模，进行了风洞试验。结果表明，在常规高超声速风洞流场中圆锥三维边界层存在定常横流涡、低频和高频不稳定波；有迎角 条件下，低频(15~50 kHz)和高频(210~340 kHz)不稳定波同时存在，圆锥边界层更容易发生转捩。随着迎角的增加，定常横流涡“条带”结构更加清晰，模型尾段的转捩阵面向迎风面移动，低频和高频不稳定波振幅增大、频带范围变宽；同一迎角下，增大单位雷诺数，高频、低频不稳定波和定常横流涡更早地出现并增长至饱和，伴随着不稳定波的振幅增大和频带变宽，其中低频不稳定波相较于高频不稳定波更早出现。.本项目成果有利于为高超声速三维边界层转捩的精确预估、转捩有效控制方法及转捩物理机理研究提供理论基础，为宽速域高超声速飞行器的精细化设计提供技术支撑。

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