摘要
采用大涡模拟与声类比的方法研究了尾缘锯齿对翼型自噪声的影响。以SD2030翼型为研究对象,设计的尾缘锯齿幅值为10%弦长,周期为4%弦长。模拟了来流速度为31m/s、0°攻角下直尾缘翼型与锯齿尾缘翼型的流场,对应的基于弦长的雷诺数约为310 000。详细分析了尾缘锯齿对翼型尾缘湍流流场的影响,并通过FW-H方程计算大涡模拟提取的声源项,得到直尾缘翼型与锯齿尾缘翼型的声场。研究发现,锯齿尾缘可以明显降低翼型中低频范围内的噪声,在4 000Hz以下,窄带噪声最多可降低约16dB。但尾缘锯齿对翼型气动性能有着不利影响。进一步研究表明,该状态下翼型噪声主要由层流边界层引起的涡脱落噪声主导,尾缘锯齿可以抑制层流边界层引起的涡脱落现象,降低翼型升力脉动与尾缘附近的表面压力脉动,减弱尾缘处的低频湍流脉动与涡量,并有效降低尾缘附近涡的展向相关性,这些因素的综合作用使得翼型自噪声降低。
Large eddy simulation and acoustic analogy are performed to investigate the effects of trailing edge serrations on airfoil self-noise. A SD2030 airfoil is used for study. The trailing edge serrations; amplitude is 10 % of airfoil chord while the serrations; wavelength is 4% of airfoil chord. The fluid field of SD2030 airfoil at 0; angle of attack with incoming flow velocity of 31 m/s is simulated and the corresponding Reynolds number based on airfoil chord is about 310 000. The effect of trailing edge serrations on the turbulence flow field near the airfoil trailing edge is analyzed in detail. Then FW-H equation is used to calculate the sound field of the straight/serrated trailing edge airfoil with the help of the sound source information obtained by the large eddy simulation. It is found that trailing edge serrations can significantly reduce airfoil noise in low to mid- dle frequency range. The noise reduction can reach up to 16 dB in narrow band in the frequency range smaller than 4 000 Hz. However, the airfoil aerodynamic performance is adversely affected by the trailing edge serration. Further results show that the airfoil noise is dominated by laminar boundary layer-vortex shedding noise under the current condition. It is found that the trailing edge serrations can suppress the laminar boundary layer-vortex shedding phenomenon and reduce the surface pressure fluctuation near the airfoil trailing edge as well as airfoil lift fluctuation. In addition, the turbulent fluctuation at low frequency and the vorticity near the trailing edge are reduced. The vortex spanwise correlation is also decreased near the trailing edge. These factors work jointly and lead to the final airfoil self-noise reduction.
出处
《航空学报》
EI
CAS
CSCD
北大核心
2015年第9期2911-2922,共12页
Acta Aeronautica et Astronautica Sinica
基金
国家自然科学基金(51276149)
空气动力学国家重点实验室研究基金(SKLA20140201)~~
关键词
翼型自噪声
涡脱落噪声
宽频噪声
仿生学
尾缘锯齿
airfoil self-neise
vortex shedding noise
broadband noise
bionics
trailing edge serrations
