实验流体力学2025，Vol.39Issue(5)：73-79,7.DOI:10.11729/syltlx20220106
直升机机体表面声载荷试验研究
Experimental research on surface acoustic load of helicopter fuselage
刘少腾 1刘向楠 1邵天双 1丁存伟 1于文凯1
作者信息
- 1. 中国航空工业空气动力研究院 空气动力噪声及其控制黑龙江省重点实验室,哈尔滨 150001||中国航空工业空气动力研究院 低速高雷诺数航空科技重点实验室,哈尔滨 150001
- 折叠
摘要
Abstract
In order to obtain the characteristics of acoustic load on helicopter fuselage surface under complex flow field conditions,16 microphones were arranged at different positions on the outer surface of the fuselage,and date from all channels were synchronously collected by a high-speed parallel acquisition system with a sampling frequency of 40.96 kHz.Using the rotor/body interaction model,the fuselage surface acoustic load test was carried out in the FL-10 wind tunnel.The test results show that the surface acoustic load of the helicopter fuselage increases with the increase of the collective pitch and forward flight speed;the rotating noise and broadband noise can be clearly captured on the surface of the helicopter fuselage;when the helicopter is in sloping descent,the noise of the blade vortex interaction can be clearly measured on the surface of the fuselage.关键词
直升机/机体/表面声载荷/风洞试验Key words
helicopter/fuselage/surface acoustic load/wind tunnel test引用本文复制引用
刘少腾,刘向楠,邵天双,丁存伟,于文凯..直升机机体表面声载荷试验研究[J].实验流体力学,2025,39(5):73-79,7.
