摘要
依据翼型理论分别提取四种鸟类翅膀沿展向40%截面处的翼型,采用大涡模拟结合声类比的FW-H方程的方法对不同仿生翼型进行流场及声场的模拟。非定常流场的计算结果表明,在逆压梯度作用下,气流在叶片吸力面前缘开始分离;在叶片下游处产生了明显的涡结构,脱离叶片尾缘后涡结构发生破碎。在四种仿生翼型中,海鸥翼型的升阻比最大,鹗翼的升阻比最小,但鹗翼具有优良的降噪特性。声压级的方向性分布揭示了仿生翼型声源具有偶极子声源特性。
The bionic airfoils were restructured by extracting cross-section configurations of four species of bird wings at the 40%position along the spanwise direction respectively based on the airfoil theory.The flow fields and the corresponding sound fields over the designed bionic airfoils were simulated numerically by using large-eddy simulation coupled with the acoustic analogy of Ffowcs-Williams and Hawkings equation.The results on unsteady flow simulations indicated that the airflow separated at the leading edge of the suction side under the effect of adverse pressure.The vortex structure was formed at the downstream of the blade,and it broke down after it was separated from the tailing edge of the blade.The lift-to-drag ratio of seagull airfoil was the maximum and the lift-to-drag ratio of owl airfoil was the minimum,however,the later possessed excellent noise-reduction characteristic.The directional distribution of SPL revealed the dipole characteristics of the acoustic source of four bionic airfoils.
出处
《工程热物理学报》
EI
CAS
CSCD
北大核心
2015年第12期2629-2632,共4页
Journal of Engineering Thermophysics
基金
高等学校博士学科点专项科研基金项目(No.20120201110064)
陕西省科学技术研究发展计划项目(No.2014K06-24)
关键词
仿生翼型
大涡模拟
气动噪声
升阻比
bionic airfoil
large eddy simulation
aerodynamic noise
lift-to-drag ratio
