Delft Parametric Flutter Margin (PFM) Test Data Archive

The dataset corresponds to the supplementary data for the paper titled 'Safe Flutter Determination for Wings Undergoing Large Deflections' (link: https://arc.aiaa.org/eprint/HDIFICQ9BW3BMFT2ZAAM/full/10.2514/6.2023-0379) and the MSc thesis entitled 'Safe Flutter Determination for Wings Undergoing Large Deflections' (link: http://resolver.tudelft.nl/uuid:b0e12214-ca2a-4dde-8499-955d2da08937). <br> The dataset contains wind tunnel test data acquired for the validation of a new flutter test version of the Parametric Flutter Margin (PFM) method, specifically applied to wings undergoing large deflections. The PFM method adds a stabilising parameter, such as a stabilising mass, to the model such that the flutter velocity is increased. To demonstrate the method a wind tunnel test campaign was performed at TU Delft using the Delft Pazy Wing which can exhibit large nonlinear deflection. The wing was equipped with a flutter pod consisting of a shaker and stabilising mass that was placed at the mid-span position at the leading edge of the wing. During the test campaign, three test series were performed. The first identified the flutter boundary through direct flutter tests, with the flutter onset and offset velocities being determined by actually hitting flutter that turned into a Limit Cycle Oscillation (LCO). The second and third test series were the PFM measurements, where both Single Input Single Output (SISO) and Multiple Input Multiple Output (MIMO) PFM tests were applied to obtain the nominal flutter boundaries without actually hitting flutter. <br>

本数据集对应题为《大变形机翼安全颤振判定》（Safe Flutter Determination for Wings Undergoing Large Deflections）的学术论文及其补充数据，论文链接为：https://arc.aiaa.org/eprint/HDIFICQ9BW3BMFT2ZAAM/full/10.2514/6.2023-0379；同时对应题为《大变形机翼安全颤振判定》（Safe Flutter Determination for Wings Undergoing Large Deflections）的硕士学位论文，其链接为：http://resolver.tudelft.nl/uuid:b0e12214-ca2a-4dde-8499-955d2da08937。
本数据集包含用于验证参数化颤振裕度（Parametric Flutter Margin, PFM）方法新型试验版本的风洞试验数据，该方法专门针对发生大变形的机翼开发。PFM方法通过为试验模型添加稳定参数（如稳定配重）以提升颤振临界速度。为验证该方法，研究团队在代尔夫特理工大学（TU Delft）开展了风洞试验，试验对象为可产生大幅非线性变形的代尔夫特帕齐机翼（Delft Pazy Wing）。该机翼于翼展中点前缘位置安装了由激振器与稳定配重组成的颤振舱。本次试验共开展三组试验：第一组通过直接颤振试验辨识颤振边界，通过实际触发颤振并使其演变为极限环振荡（Limit Cycle Oscillation, LCO）来确定颤振起始与终止速度；第二组与第三组为PFM测量试验，分别采用单输入单输出（Single Input Single Output, SISO）与多输入多输出（Multiple Input Multiple Output, MIMO）两种PFM测试方案，在未实际触发颤振的前提下获取名义颤振边界。