Direct self-noise simulation of the installed Controlled Diffusion airfoil
Direct self-noise simulation of the installed Controlled Diffusion airfoil
复制标题
对已安装的受控扩散翼型进行直接自噪声模拟
DOI：
10.2514/6.2011-2716
复制
发表时间：
2011
影响因子：
3.6
通讯作者：
Min
中科院分区：
文献类型：
--
作者：
S. Moreau;M. Sanjosé;F. Pérot;Min
使用格子-玻尔兹曼方法 (PowerFlow) 直接模拟受控扩散 (CD) 翼型后缘产生的宽带噪声，该方法可解析翼型周围的空气动力场和声场。首先在模型的准二维切片上的机翼附近实现正确的 DNS 解析。然后将其扩展到跨度为 12% 弦长的 3D 切片。研究了消声开放喷射装置的两个数值设置，其中收集了空气动力学和声学数据，以捕获安装效果：在第一个数值设置（称为自由）中，CD翼型设置为均匀流，而在第二个设置（唇缘）中，考虑真实的喷嘴几何形状。在自由场配置中，边界层在吸力侧快速分离，而在唇部中，射流剪切层改变翼型上的压力载荷，并且边界层在带有喷嘴的配置中保持附着。在这两种设置中，层流再循环气泡在前缘附近的吸力侧被捕获，这触发了沿吸力侧的边界层的发展。自由配置的壁压和噪声谱分布在一个大频带上，并且与流分离的较高攻角下的类似测量结果一致。嘴唇结构的光谱与实验数据更加吻合，并已被选择用于 3D 模拟。先前研究的设置中缺少沿翼展方向拉伸的涡流，可以仅捕获湍流长度尺度并准确地再现实验测量结果。边界层轮廓和后缘附近的壁压力谱都被很好地、准确地捕获。预测的法菲尔德声压级也与消声风洞中的噪声测量结果令人满意地一致。
Broadband noise produced by the trailing-edge of a controlled di usion (CD) airfoil is directly simulated using a Lattice-Boltzmann method (PowerFlow) that resolves both the aerodynamic and acoustic eld around the airfoil. The proper DNS resolution is rst achieved in the vicinity of the airfoil on a quasi-2D slice of the mock-up. It is then extended to a 3D slice with a span of 12 % chord length. Two numerical setups of the anechoic openjet facility where both aerodynamic and acoustic data have been collected are investigated to capture the installation e ects: in a rst numerical setup (called free), the CD airfoil is set in an uniform ow, while in the second setup (lips) the real jet nozzle geometry is considered. While in the freeeld con guration the boundary layer rapidly detaches on the suction side, in the lips the jet shear layers modify the pressure load on the airfoil and the boundary layer keeps attached in the con guration with nozzle. In both setups a laminar recirculation bubble is captured on the suction side near the leading edge which triggered the development of the boundary layers along the suction side. The wall-pressure and noise spectra for the free con guration are spread over a large frequency band and agree with similar measurements at higher angle of attack for which the ow is detached. The spectra for the lips con guration better agree with the experimental data and has been selected for the 3D simulation. The vortex stretching along the span-wise direction that was missing in the previous investigated set-ups, allows to nely capture the turbulence length scales and accurately reproduce the experimental measurements. Both the boundary layer pro le and the wall pressure spectra near the trailing edge are nicely and accurately captured. The predicted fareld sound pressure levels also provide satisfactory agreement with noise measurements in the anechoic wind tunnel.
影响因子：
4.7
作者：
R. Sandberg;L. E. Jones;N. Sandham;P. Joseph
通讯作者：
R. Sandberg;L. E. Jones;N. Sandham;P. Joseph