摘要
气动噪声水平是衡量民用客机设计水平的重要指标之一。在飞机着陆过程中,增升装置缝翼是机体气动噪声的重要噪声源。通过求解非线性扰动方程对增升装置缝翼噪声进行了二维数值模拟研究。分别针对不同来流攻角以及主翼钝后缘和尖后缘研究了缝翼噪音的频率特性。计算结果表明,缝翼缝道内的非定常涡是产生噪声的主要原因,随着来流攻角的减小,缝道内的非定常涡强度增大,活动区域变宽,进而辐射更多的噪声,从非定常声场及噪声的频率特性来看,缝翼噪声是一种偶极子声源,具有明显的宽频特性,主要噪声源集中在低频到中频段,随着频率增大,噪声幅值逐渐衰减。数值模拟较好地捕捉到了缝翼噪声源的发声机制和频率特性,为噪声控制打下了良好的基础。
The aeroacoustics level is one of the most important criterions for civil aircraft design. The slat noise is a dominating noise component during the aircraft landing. In this paper, the numerical simulation research of the slat noise frequency characteristic aiming to different angle of attack and blunt/sharp main trailing edge was done by solving the unlinear disturbance equation in two dimensional. The results show that the unsteady vorticity in the slat cove causes the noise . As the angle of attack decreased, the strength of the unsteady vorticity increased with the extent broadening and radiate more noise. It could be seen from the unsteady acoustic field and frequency characteristic that the slat noise is a kind of dipole source with broadband characteristic. The dominating noise component arose in low and mid frequency. The noise amplitude decreased as the frequency increased. The physics and fre-quency characteristic is well captured by numerical simulation which makes a good foundation for noise control.
出处
《民用飞机设计与研究》
2014年第4期21-26,86,共7页
Civil Aircraft Design & Research
关键词
气动噪声
增升装置
大型客机
数值模拟
aeroacoustics
high lift device
large civil transport
numerical simulation
