NACA-65-0012振荡机翼远场气动噪声的预测研究  

Numerical investigation of aerodynamic noise generated by the oscillating NACA-65-0012 airfoil

作　　者：杨爱玲[1] 陈康民[1] 

机构地区：[1]上海理工大学能源与动力工程学院,上海200093

出　　处：《上海理工大学学报》2009年第2期145-149,共5页Journal of University of Shanghai For Science and Technology

基　　金：上海市教育委员会资助项目(05ZZ27);高等学校博士学科点专项基金资助项目(20060252007)

摘　　要：基于声波发射时间编写了远场噪声预测的Kirchhoff积分程序,并通过静止介质中的静止点声源与匀速运动点声源的远场噪声预测验证了积分程序的可靠性.结果表明,该Kirchhoff积分程序可以获得远场噪声的有效声压和声场指向性分布.在来流马赫数为0.5且不计黏性的条件下,结合非定常流场计算程序与Kirchhoff积分程序对二维孤立振荡叶型诱发的远场噪声进行数值预测,获得了远场观察者的瞬时声压和声场指向性分布.研究表明,在30°,120°,210°和315°方向声压有效值较大.For avoiding a great deal of interpolating calculation and data saving, the sound pressure at the place of the observer was integrated at the emission time of sound wave to avoid a great of interpolating calculation and data saving. At first, the code of Kirchhoff method was validated by the prediction of sound pressure generated by a moving sound source at Mach number 0.5. The results show that the Kirchhoff code can predict well the pressure and directivity patterns except the phase error. Then the sound pressure generated by an NACA-65-0012 airfoil, which is oscillating in uniform flow at 0.5 Mach number, was estimated. To obtain the sound sources, the unsteady Euler equation was solved with fourth order Runge-Kutta scheme and Roe Scheme. The distribution of sound pressure at the place of observers show that the radiation of the sound wave is of more strength at 30°, 120° ,210°and 315°.

关 键 词：气动噪声 KIRCHHOFF积分法 指向性分布 振荡机翼 

分 类 号：O35[理学—流体力学]