Data from the experimental measurement of a pitching airfoil NACA643418

The present experimental work is motivated by the need for a fundamental understanding of the vortex-induced vibrations (VIV) of airfoils at high angles of attack from an aerodynamic perspective. The dynamic stall of a pitching NACA 643418 airfoil was investigated under reverse flow conditions, whereby the geometric trailing edge is located upstream of the geometric leading edge. The investigation focuses on the correlation between surface pressure, aerodynamic forces, and the evolution of the dynamic stall vortex (DSV) and the aerodynamic trailing edge vortex (TEV). A range of mean angles of attack from 5° to 25°, pitching amplitudes from 5° to 15°, and reduced frequencies between 0.05 and 0.21 were tested on an airfoil using a combination of particle image velocimetry (PIV) and surface pressure measurements. <br>

本实验研究旨在从空气动力学视角，深入理解高攻角下翼型涡激振动（vortex-induced vibrations, VIV）的内在机理。针对逆流工况下做俯仰运动的NACA 643418翼型的动态失速（dynamic stall）现象展开研究，该工况中翼型的几何后缘位于几何前缘的上游。本次研究聚焦于表面压力、气动力与动态失速涡（dynamic stall vortex, DSV）、气动后缘涡（aerodynamic trailing edge vortex, TEV）演化过程之间的关联规律。试验采用粒子图像测速技术（particle image velocimetry, PIV）与表面压力测量相结合的方案，对平均攻角范围为5°~25°、俯仰幅值范围为5°~15°、折减频率范围为0.05~0.21的翼型工况开展了测试。