全尺寸涡桨飞机起落架气动噪声及控制试验研究
Experimental Study on Full Scale Turbo-prop Landing Gear Noise and Control Method
包安宇 1徐文强 1刘少腾 1陈宝 1周国成 1丁存伟1
作者信息
- 1. 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,黑龙江 哈尔滨 150001;黑龙江省空气动力噪声及其控制实验室,黑龙江 哈尔滨 150001
- 折叠
摘要
本文在2m航空声学风洞开展了全尺寸涡桨飞机起落架气动噪声风洞试验研究,研究内容包含有无噪声控制措施下的气动噪声特性,测量内容包含静压测量、脉动压力测量、表面声载荷、1/3圆弧线阵指向性测量、远场壁面线阵测量以及水平竖直面阵声源定位研究,采用多种测量手段从气动和噪声角度解释了起落架噪声控制措施对远场噪声特性的影响.试验结果表明,起落架凹腔填充可以有效控制空腔自激振荡引起的纯音,从而降低起落架噪声总体水平.
Abstract
An experimental research on simplified turbo-prop aircraft landing gear noise was carried out in 2m aero-acoustic wind tunnel to study the characteristic of baseline and noise control strategy,the measurement content includes steady pressure,dynamic pressure,surface acoustic loading,1/3 polar arc directivity,far-field wall directivity array,horizontal and vertical phased array.The influence of noise control strategy on noise characteristic is explained from aerodynamic and aero-acoustic aspect.Test results verified that cavity filament can reduce the overall noise level by cancelling the Rossiter-type tone nosie.
关键词
涡桨飞机/起落架/气动噪声/声源定位/噪声控制Key words
turbo-prop/landing gear/aero-acoustic/source localization/noise control引用本文复制引用
出版年
2024
NETL
NSTL
万方数据