Author:
Zhang Qi,Bodony Daniel J.
Abstract
Direct numerical simulations are used to study the interaction of a cavity-backed circular orifice with grazing laminar and turbulent boundary layers and incident sound waves. The flow conditions and geometry are representative of single degree-of-freedom acoustic liners applied in the inlet and exhaust ducts of aircraft engines and are the same as those from experiments conducted at NASA Langley. The simulations identify the fluid mechanics of how the sound field and state of the grazing boundary layer impact the in-orifice flow and suggest a simple flow analogy that enables scaling estimates. From the scaling estimates the simulations are then used to develop reduced-order models for the in-orifice flow and a time-domain impedance model is constructed. The liner is found to increase drag at all conditions studied by an amount that increases with the incident sound pressure amplitude.
Publisher
Cambridge University Press (CUP)
Subject
Mechanical Engineering,Mechanics of Materials,Condensed Matter Physics
Reference74 articles.
1. The acoustic impendance of perforates at medium and high sound pressure levels
2. Time-domain impedance boundary conditions for computational aeroacoustics
3. Zhang, Q. 2014 Direct numerical investigation and reduced-order modeling of 3-D honeycomb acoustic liners. PhD thesis, University of Illinois at Urbana-Champaign.
4. Sherer, S. E. , Visbal, M. R. & Galbraith, M. C. 2006 Automated preprocessing tools for use with a high-order overset-grid algorithm. In AIAA Paper 2006-1147, Presented at the 44th Aerospace Sciences Meeting and Exhibit, Reno, NV, January, AIAA.
Cited by
66 articles.
订阅此论文施引文献
订阅此论文施引文献,注册后可以免费订阅5篇论文的施引文献,订阅后可以查看论文全部施引文献