旋翼跨声速流动气动噪声的一种高效算法  

A High Efficiency Method for Calculating the Aeroacoustic Noise of Transonic Rotors

作　　者：宋文萍[1] 韩忠华[1] 杨爱明[1] 乔志德[1] 

机构地区：[1]西北工业大学翼型研究中心,陕西西安710072

出　　处：《西北工业大学学报》2001年第4期515-519,共5页Journal of Northwestern Polytechnical University

基　　金：航空科学基金 (98A5 30 0 2 );国家重点实验室基金 (98JS5 1.3.1.ZS5 10 3)

摘　　要：采用 Euler/Kirchhoff方法 ,计算了直升机旋翼悬停流场的远场噪声。在采用 CFD方法求解非定常旋翼悬停流动的 Euler方程的基础上 ,采用 Kirchhoff公式计算了直升机悬停流动的远场噪声。文中对 Kirchhoff面的选取、声源点延迟时刻的确定方法进行了研究 ,并提出了一种由 Euler方程解确定 Kirchhoff面上物理参数及其空间法向导数的高效三维线性插值方法。对 UH- 1 H直升机旋翼跨声速悬停流动的远场噪声进行了定量计算 ,计算结果与实验值相比较 ,符合较好 ,验证了本文方法的正确性。Starting from our previous solution of the 3-D unsteady Euler equation of hovering rotor flow, we discuss in subsection 1.2 how to compute far field noise by Kirchhoff formula. In subsubsections 1.2.2 and 1.2.3 we discuss how to interpolate sonic pressure, its spatial derivative and its time derivative on the Kirchhoff surface. In subsubsection 1.2.3 we put forward a highly efficient 3-D linear interpolation method. Refs. and used UH-1H helicopter rotor as numerical example. We also take UH-1H rotor as our numerical example. Figs.4, 5 and 6 show preliminarily that our computed results are in good agreement with experimental data. Fig.8 shows preliminarily that choice of position of Kirchhoff surface has some effect on the computed results of sonic pressure.

关 键 词：旋翼 欧拉方程 气动噪声 Kirchhoff公式 直升机 跨声速流动 计算 

分 类 号：V211.52[航空宇航科学与技术—航空宇航推进理论与工程]