Computational aeroelastic analysis of a hovering W3 Sokol blade with gurney flap

This paper demonstrates the potential effect of a gurney flap on the performance of the W3-Sokol rotor blade in hover. A rigid blade was first considered and the calculations were conducted at several thrust settings. The gurney flap was extended from 46%R to 66%R and it was located at the trailing edge of the main rotor blade. Four different sizes of gurney flaps were studied, 2%, 1%, 0.5% and 0.3% of the chord. The biggest flap proved to be the most effective. A second study considered elastic blades with and without the gurney flap. The results were trimmed at the same thrust values as the rigid blade and indicate an increase of aerodynamic performance when the gurney flap is used, especially for high thrust cases.     

Effects of Gurney Flaps on a NACA0012 Airfoil

Experimental measurements of surface pressure distributions and wake profiles were obtained for a NACA0012 airfoil to determine the lift, drag, and pitching-moment coefficients for various configurations. The addition of a Gurney flap increased the maximum lift coefficient from 1.37 to 1.74, however there was a drag increment at low-to-moderate lift coefficient. In addition, the boundary layer profile measurements were taken using a rake of total pressure probes at the 90% chord location on the suction side. The effective Gurney flap height is about 2% of chord length, which provides the highest lift-to-drag ratio among the investigated configurations when compared with the clean NACA0012 airfoil. In this case, the device remains within the boundary layer. This revised version was published online in July 2006 with corrections to the Cover Date.     

南线A污水泵站浑水模型试验研究

在城市合流污水泵站普遍存在着严重程度不同的泥沙淤积问题，对泥沙输移、沉积研究较多的是明渠、河道、河口、海洋、港口等，而对泵站前池、高位井泥沙沉积、冲淤的研究仍多为定性分析。本文通过选用人工轻质沙电木屑，即通过降低模型沙的比重来相对增大粒径，达到模型和原型冲淤相似。对南线A污水泵站进行浑水模型试验，研究分析污水中固体颗粒在泵站前池和高位井中输移、沉降和冲淤规律，发现原设计方案前池固体颗粒淤积较严重，提出前池设置导流墩、倾角为45°的压水板和垂直挡水板相应的优化方案，均不同程度获得前池较好的流态，固体颗粒淤积也有较大减少。     

直升机旋翼挥舞、摆振的激光动态测试系统

提出一种直升机旋翼挥舞、摆振角的动态测试系统。在直升机桨毂安装与旋翼同步旋转的三叉件 ,每个三叉件悬臂上装有光学三角位移传感器和线阵 CCD位移传感器 ,实现了动态测量直升机旋翼桨叶的挥舞和摆振角。为保证系统在恶劣条件下正常工作 ,系统采用了加装干涉滤光片、L D调制技术和自动增益控制电路等一系列技术措施。最后给出了实验结果。由位移 -角度转换和传感器自身的非线性引起的误差用若干静态标定点为节点插值的方法修正。得到较高精度的测试曲线     

开槽扰流片流动特性研究

用标准的k-ε湍流方程结合近壁流动的两层带状模型,在非结构网格上采用SIMPLE算法,对不同开孔度的开槽扰流片流动特性进行了数值模拟,并和测压实验结果进行了比较.结果表明开槽扰流片的流动结构取决于上下两部分流场的相互耦合作用,开孔度η=50%时两个流场互相没有干扰,开孔度η=20%,30%时两个流场相互耦合作用很强,扰流片后有较大的回流区以及较小的湍流动能.     

Dynamical mode decomposition of Gurney flap wake flow

The present work uses dynamic mode decomposition (DMD) to analyze wake flow of NACA0015 airfoil with Gurney flap. The physics of DMD is first introduced. Then the PIV-measured wake flow velocity field is decomposed into dynamical modes. The vortex shedding pattern behind the trailing edge and its high-order harmonics have been captured with abundant information such as frequency, wavelength and convection speed. It is observed that high-order dynamic modes convect faster than low-order modes; moreover the wavelength of the dynamic modes scales with the corresponding frequency in power law.