Interaction of a Shock wave with a Homogeneous Field of Acoustic Waves: Theory and Simulation

冲击波与均匀声波场的相互作用：理论与模拟

• 批准号: 2001125
• 负责人: Lian Duan
• 金额: $ 16.03万
• 依托单位: Ohio State University
• 依托单位国家: 美国
• 项目类别: Continuing Grant
• 财政年份: 2019
• 资助国家: 美国
• 起止时间: 2019-09-23 至 2022-08-31
• 项目状态: 已结题
• 来源: https://www.nsf.gov/awardsearch/showAward?AWD_ID=2001125&HistoricalAwards=false
• 关键词: Interaction; Shock; wave; Homogeneous; Field

A shock wave occurs when a wave moves faster than the speed of sound in a fluid. The interaction of a shock wave with compressible turbulence is relevant to a wide range of engineering applications including aeronautics (supersonic flight and propulsion), energy (fusion), medicine (shock wave lithotripsy), and space physics (star formation and supernovae explosions). Understanding the physics of the interaction between a shock wave and a homogeneous field of acoustic waves (shock/acoustics interaction) are of major theoretical and practical importance. Given that the coexistence of shock waves with background acoustic noise is an almost unavoidable feature for any experiments conducted in supersonic wind tunnels, the study of shock/acoustics interaction is particularly important to the characterization of background acoustic disturbances in supersonic wind tunnels and to the extrapolation of measurement data obtained in noisy supersonic wind tunnels to free flight. The experiences and results gained from the research effort are being incorporated into education activities including classroom teaching, research training, and outreach activities via involvement in Missouri S&T Student Diversity, Outreach and Women?s Programs in order to engage students to consider careers in STEM fields. In this research project, significant flow characteristics associated with a homogeneous field of acoustic waves passing through a nominally normal shock wave are quantified using direct numerical simulations and linear interaction analysis. The full-fledged nonlinear simulations and the linear analysis are enabled by a pre-cursor numerical database of boundary-layer acoustic radiation that provides incident acoustic fields with a high degree of physical realism and applicability. This study advances the state of the art knowledge of shock/acoustics interaction, including (1) the generic statistical and spectral features of the post-shock fluctuations and their dependence on flow parameters; (2) the distinctions between linear and nonlinear mechanisms; and (3) the transfer function associated with the total pressure and the contribution of individual Kovasznay modes to the post-shock total pressure. This research contributes to the fundamental understanding of the interaction of a shock wave with a field of turbulence by characterizing its behaviors in the pure dilatational limit and complements existing studies of shock/turbulence interaction with a vorticity-dominated incident turbulent field. The project also provides the basis for measuring tunnel freestream noise with intrusive probes in noisy supersonic wind tunnels and for elucidating the impact of facility noise on the experimental data obtained in such wind tunnels.

当波在流体中的传播速度超过声速时，就会产生冲击波。激波与可压缩湍流的相互作用与广泛的工程应用相关，包括航空（超音速飞行和推进），能源（聚变），医学（冲击波碎石）和空间物理（恒星形成和超新星爆炸）。了解激波和均匀声场之间相互作用的物理原理（激波/声学相互作用）具有重要的理论和实践意义。鉴于激波与背景声噪声的共存是任何超声速风洞实验中几乎不可避免的特征，激波/声学相互作用的研究对于表征超声速风洞中背景声干扰以及将有噪声的超声速风洞中获得的测量数据外推到自由飞行中尤为重要。从研究工作中获得的经验和结果被纳入教育活动，包括课堂教学，研究培训和推广活动，通过参与密苏里大学学生多样性，推广和妇女？s计划，以吸引学生考虑在STEM领域的职业生涯。在本研究项目中，通过直接数值模拟和线性相互作用分析，量化了与通过名义正常激波的均匀声波场相关的显著流动特性。边界层声辐射的前光标数值数据库提供了具有高度物理真实感和适用性的入射声场，从而实现了全面的非线性模拟和线性分析。这项研究推进了激波/声学相互作用的最新知识，包括：(1)激波后波动的一般统计和频谱特征及其对流动参数的依赖；(2)线性和非线性机构的区别；(3)与总压力相关的传递函数以及各个Kovasznay模态对冲击后总压力的贡献。该研究通过描述激波在纯膨胀极限下的行为，有助于对激波与湍流场相互作用的基本理解，并补充了现有的激波/湍流相互作用与涡度主导的入射湍流场的研究。为在含噪超声速风洞中使用侵入式探头测量风洞自由流噪声以及阐明设施噪声对风洞实验数据的影响提供了依据。

项目成果

Interaction of a Tunnel-like Acoustic Disturbance Field with a Blunt Cone Boundary Layer at Mach 8

8 马赫时隧道状声扰场与钝锥边界层的相互作用

• DOI: 10.2514/6.2022-3250
• 发表时间: 2022
• 期刊: AIAA AVIATION 2022 Forum
• 作者: Liu, Yuchen;Schuabb, Mateus;Duan, Lian;Paredes, Pedro;Choudhari, Meelan M.
• 通讯作者: Choudhari, Meelan M.

Characterization of Freestream Disturbances in Conventional Hypersonic Wind Tunnels

传统高超声速风洞中自由流扰动的表征

• DOI: 10.2514/1.a34290
• 发表时间: 2019
• 期刊: Journal of Spacecraft and Rockets
• 影响因子: 1.6
• 作者: Duan, Lian;Choudhari, Meelan M.;Chou, Amanda;Munoz, Federico;Radespiel, Rolf;Schilden, Thomas;Schröder, Wolfgang;Marineau, Eric C.;Casper, Katya M.;Chaudhry, Ross S.
• 通讯作者: Chaudhry, Ross S.

On the Nature of Freestream Disturbances in a Two-Dimensional Supersonic Test Section

二维超声速试验段自由流扰动的本质

• DOI: 10.2514/6.2021-0162
• 发表时间: 2021
• 期刊: AIAA Scitech 2021 Forum
• 作者: Prasad, Chitrarth;Huang, Junji;Duan, Lian;Gaitonde, Datta V.
• 通讯作者: Gaitonde, Datta V.

Interaction of a Tunnel-like Acoustic Disturbance Field with a Normal Shock Wave: Theory and Simulation

隧道状声扰场与法向冲击波的相互作用：理论与仿真

• DOI: 10.2514/6.2022-3410
• 发表时间: 2022
• 期刊: AIAA AVIATION 2022 Forum
• 作者: Liu, Yuchen;Duan, Lian
• 通讯作者: Duan, Lian

Supersonic transition induced by numerical tunnel disturbances

数值隧道扰动引起的超音速转变

• DOI: 10.2514/6.2022-1826
• 发表时间: 2022
• 期刊: AIAA SCITECH 2022 Forum
• 作者: Goparaju, Hemanth;Liu, Yuchen;Duan, Lian;Gaitonde, Datta V.
• 通讯作者: Gaitonde, Datta V.