Vortex Shedding from Airfoils in Reverse Flow
Vortex Shedding from Airfoils in Reverse Flow
复制标题
DOI：
10.2514/1.j053764
复制
发表时间：
2015-07
期刊：
影响因子：
2.5
通讯作者：
A. Lind;Anya R. Jones
中科院分区：
文献类型：
--
作者：
A. Lind;Anya R. Jones
给出了三种翼型在360°静态迎角下的旋涡脱落特性，重点研究了反向流动(150≤α≤，180°)。风洞试验是在一个具有尖锐后缘的翼型(NACA 0012)和两个具有钝化后缘的翼型(椭圆和DBLN-526)上进行的。采用时间分辨粒子图像测速仪和烟流显示技术，对细长体涡脱落、湍流和深失速涡脱落三种逆流尾迹进行了识别。细长机身区域存在于小迎角和低雷诺数时。在湍流区，分离发生在NACA 0012尖锐的气动前缘的反向流动中，而流动分离发生在翼型弦下更远的地方，具有钝化的几何后缘。利用非定常测力天平测量了深失速旋涡脱落频率。斯特劳哈尔数Std(基于翼型的投影直径d)被发现是0.145-...
The vortex shedding characteristics of three airfoils held at static angles of attack through 360 deg are presented with a focus on reverse flow (150≤α≤180 deg). Wind tunnel testing was performed on one airfoil with a sharp trailing edge (NACA 0012) and two airfoils featuring a blunt trailing edge (ellipse and DBLN-526). Time-resolved particle image velocimetry and smoke flow visualization were used to identify three reverse flow wake regimes: slender body vortex shedding, turbulent, and deep stall vortex shedding. The slender body regime is present for low angles of attack and low Reynolds numbers. In the turbulent regime, separation occurs in reverse flow at the sharp aerodynamic leading edge of a NACA 0012, whereas flow separation occurs further down the chord of airfoils with a blunt geometric trailing edge. The deep stall vortex shedding frequency was measured using unsteady force balance measurements. The Strouhal number Std (based on the projected diameter d of the airfoils) was found to be 0.145–...