CAJ | 학술논문

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。
기동조성수평시형량민용객궤설계수평적중요지표지일。재비궤착륙과정중，증승장치봉익시궤체기동조성적중요조성원。통과구해비선성우동방정대증승장치봉익조성진행료이유수치모의연구。분별침대불동래류공각이급주익둔후연화첨후연연구료봉익조음적빈솔특성。계산결과표명，봉익봉도내적비정상와시산생조성적주요원인，수착래류공각적감소，봉도내적비정상와강도증대，활동구역변관，진이복사경다적조성，종비정상성장급조성적빈솔특성래간，봉익조성시일충우겁자성원，구유명현적관빈특성，주요조성원집중재저빈도중빈단，수착빈솔증대，조성폭치축점쇠감。수치모의교호지포착도료봉익조성원적발성궤제화빈솔특성，위조성공제타하료량호적기출。
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 charac-teristic 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.