杨党国, 刘俊, 王显圣, 施傲, 周方奇, 郑晓东. 典型构型空腔模型设计与流动/噪声特性研究[J]. 空气动力学学报, 2018, 36(3): 432-439,448. DOI: 10.7638/kqdlxxb-2017.0201
引用本文: 杨党国, 刘俊, 王显圣, 施傲, 周方奇, 郑晓东. 典型构型空腔模型设计与流动/噪声特性研究[J]. 空气动力学学报, 2018, 36(3): 432-439,448. DOI: 10.7638/kqdlxxb-2017.0201
YANG Dangguo, LIU Jun, WANG Xiansheng, SHI Ao, ZHOU Fangqi, ZHENG Xiaodong. Analysis of design method and aeroacoustics characteristics inside typical cavity[J]. ACTA AERODYNAMICA SINICA, 2018, 36(3): 432-439,448. DOI: 10.7638/kqdlxxb-2017.0201
Citation: YANG Dangguo, LIU Jun, WANG Xiansheng, SHI Ao, ZHOU Fangqi, ZHENG Xiaodong. Analysis of design method and aeroacoustics characteristics inside typical cavity[J]. ACTA AERODYNAMICA SINICA, 2018, 36(3): 432-439,448. DOI: 10.7638/kqdlxxb-2017.0201

典型构型空腔模型设计与流动/噪声特性研究

Analysis of design method and aeroacoustics characteristics inside typical cavity

  • 摘要: 空腔高速流动包含着复杂波系、旋涡、剪切层等空气动力学典型流动特征,空腔研究中的模型设计、来流马赫数和边界层等参数模拟,以及典型空腔流动/噪声计算与试验结果的差异、缘由等问题亟需解决。综合参考国内外空腔模型参数选取和设计方案,在分析前期前缘平板尖劈构型和角度对来流边界层形态和厚度的影响规律的基础上,通过改变空腔前缘平板尖劈构型和角度来解决上述参数模拟不准和引起计算与试验结果差异等问题,提出了一种典型结构平板-空腔标模(C201)的参数选取和设计方案,给定前缘平板尖劈角度为5°,并利用理论分析、数值计算和风洞试验对该模型设计方案进行了考核验证。综合利用表面流谱、空间流场结构和静/动压测量方法等,获得了亚跨超声速条件下(Ma:0.6~2.0)C201空腔流动/噪声的基本试验数据,并深入分析了该模型的流动/噪声特性及来流马赫数、攻角等参数的影响规律,可为数值计算方法的验证、空腔流动/噪声机理分析和控制方法的构建等提供基本验证数据和借鉴依据。

     

    Abstract: Complex unsteady flow characteristics and flow-field structures occur therein high speed flow past cavities, such as waves, vortex, and shear-layer. Therefore, it is a hotspot and typical flow structure within aeronautics and astronautics research. Some characteristics are very important in the research such as the cavity test model design, the free-stream Mach number for simulation methods, the selection on boundary-layer thickness, and the differences between computational and experimental results. In consideration of the parameters selection and design method of cavities, the front plate tip configuration and angle are changed on the basis of the analysis on the influence of the front plate tip configuration on the flow characteristics and thickness of the boundary-layer. Parameters selection and design scheme for the determination of a typical plate-cavity model (C201) are presented, with the front plate tip angle of 5°. The parameters selection and design scheme for the C201 cavity model are validated by theoretical analysis, numerical simulation, and wind tunnel test. The basic experimental data about the flow and aeroacoustics characteristics of the C201 cavity model are obtained at Mach numbers of 0.6, 0.9, 1.5, and 2.0. A comprehensive analysis of the surface oil-flow, flow field structure, and pressure within the cavity is presented. Detailed investigations are conducted for the aeroacoustics characteristics and influence law of Ma and angle of attack on the flow in the cavity. The experimental results can be used for the validation of numerical simulation method and controlling method construction for cavity noise, and also can provide basic data to study noise generation mechanism.

     

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