Data underlying the publication: An experimental study of the unsteady aerodynamics of a static DU91-W2-150 airfoil at large angles of attack

The main goal of this research is to experimentally investigate the unsteady aerodynamics of a static airfoil at large angles of attack (AoA), with a focus on the wake flow dynamics, vortex shedding characteristics and airfoil loading. This dataset contains the experimental measurement of a static DU91-W2-150 airfoil in a closed wind tunnel. This experimental study tested the airfoil under a wide range of AoA from 0◦ to 310◦ at three Reynolds numbers (Re) from 2×10^5 to 8×10^5. Pressure on the airfoil surface was measured and Particle Image Velocimetry (PIV) measurements were conducted to capture the flow field in the wake.

本研究的核心目标为通过实验手段探究大攻角（Angle of Attack, AoA）下静态翼型的非定常空气动力学特性，重点关注尾流流动动力学、涡脱落特征与翼型载荷情况。本数据集包含封闭风洞环境下静态DU91-W2-150翼型的实验测量数据。本实验研究分别在3组雷诺数（Reynolds Number, Re，范围为2×10^5至8×10^5）下，对该翼型开展了0°至310°的宽攻角范围测试。研究人员测量了翼型表面的压力分布，并通过粒子图像测速法（Particle Image Velocimetry, PIV）获取了尾流区域的流场数据。