The structural motion and unsteady aerodynamic loads of a pitching airfoil model that features an actuated trailing edge flap are determined experimentally using a single measurement and data processing system. This integrated approach provides an alternative to the coordinated use of multiple measurement systems for simultaneous position and flow field measurements in large-scale fluid–structure interaction experiments. The measurements in this study are performed with a robotic PIV system using Lagrangian particle tracking. Flow field measurements are obtained by seeding the flow with helium-filled soap bubbles, while the structural measurements are performed by tracking fiducial markers on the model surface. The unsteady position and flap deflection of the airfoil model are determined from the marker tracking data by fitting a rigid body model, that accounts for the motion degrees of freedom of the airfoil model, to the measurements. For the determination of the unsteady aerodynamic loads (lift and pitching moment) from the flow field measurements, two different approaches are evaluated, that are both based on unsteady potential flow and thin airfoil theory. These methods facilitate an efficient non-intrusive load determination on unsteady airfoils and produce results that are in good agreement with reference measurements from pressure transducers.

使用单个测量和数据处理系统，通过实验确定了具有动翼后缘襟翼的俯仰翼型模型的结构运动和非稳态气动载荷。这种集成方法为在大规模流固耦合实验中同时使用位置和流场测量提供了多种测量系统协同使用的替代方法。本研究中的测量是通过使用拉格朗日粒子跟踪的机器人PIV系统执行的。流场测量是通过用氦填充的肥皂泡播种流来获得的，而结构测量是通过跟踪模型表面上的基准标记来执行的。通过拟合刚体模型，根据标记跟踪数据确定机翼模型的不稳定位置和襟翼偏转，这就说明了机翼模型的运动自由度和测量结果。为了从流场测量结果确定不稳定的空气动力载荷（升力和俯仰力矩），评估了两种不同的方法，这两种方法均基于不稳定的潜在流和薄翼型理论。这些方法有助于对不稳定翼型进行有效的非侵入式载荷确定，并产生与压力传感器的参考测量值非常一致的结果。