Experimental Fluid DynamicsNo Access

Effect of leading-edge plate controlling on subsonic cavity

State Key Laboratory of Aerodynamics, China Aerodynamics Research and Development Center, Mianyang 621000, P. R. China

High Speed Aerodynamics Research Institute, China Aerodynamics Research and Development Center, Mianyang 621000, P. R. China

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Dang-Guo Yang

State Key Laboratory of Aerodynamics, China Aerodynamics Research and Development Center, Mianyang 621000, P. R. China

High Speed Aerodynamics Research Institute, China Aerodynamics Research and Development Center, Mianyang 621000, P. R. China

E-mail Address: yangdg-cardc@163.com

Corresponding author.

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Xian-Sheng Wang

High Speed Aerodynamics Research Institute, China Aerodynamics Research and Development Center, Mianyang 621000, P. R. China

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Jun-Qiang Wu

High Speed Aerodynamics Research Institute, China Aerodynamics Research and Development Center, Mianyang 621000, P. R. China

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, and

Bo Lu

High Speed Aerodynamics Research Institute, China Aerodynamics Research and Development Center, Mianyang 621000, P. R. China

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https://doi.org/10.1142/S0217979220400901Cited by:1 (Source: Crossref)

This article is part of the issue:

Special Issue — Proceedings of the Eighth International Symposium on Physics of Fluids (ISPF8), 10–13 June, 2019, Xi'an, China

Abstract

Cavity noise caused by the high-speed airflow has been paid much attention in the field of aerospace, and the study of cavity noise suppression has an important significance on improving the safety of aircraft. Effects of the leading-edge plate on the flow and the noise of the cavity model (the ratio of length to depth is 6) at a Mach number (Ma) of 0.6 are investigated with high-speed wind tunnel experiment. The acoustic and the flow field information in the cavity are obtained with the dynamic/static pressure measurement and oil flow experiment. The result shows that the leading-edge plate can greatly lift the shear layer, raise the impact position on the back-wall area, and reduce the flux rate and intensity in the cavity. With the controlling of leading-edge plate, the static pressure and backflow area are effectively suppressed and the SPL and peak noise also fall down significantly. The leading-edge plate provides a new method for cavity noise suppression in subsonic flow condition, which can be effectively applied to flow/noise controlling of cavity structure on aircraft.

Keywords:

PACS: 47.85.1f

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