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，深入理解大攻角下翼型的涡致振动（Vortex-Induced Vibrations, VIV）的基础物理机制。本研究针对逆流工况下的俯仰运动NACA 643418翼型开展动态失速特性研究，该工况下翼型的几何后缘位于几何前缘的上游位置。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（Trailing Edge Vortex, TEV）的演化过程之间的关联机制。研究团队结合粒子图像测速法（Particle Image Velocimetry, PIV）与表面压力测量技术，对该翼型开展了系列实验测试，测试参数覆盖5°至25°的平均攻角范围、5°至15°的俯仰幅值区间以及0.05至0.21的减缩频率。