Predicting structural loads on elastic delta wing structures exhibiting complex flow phenomena is crucial for the aircraft design process. In that regard, wind tunnel experiments are essential for validating numerical simulations. To ensure comparability concerning full-scale applications, the consideration of elastically scaled, deformable wings plays an important role. This work investigates such a design for a 3D-printed half-model delta wing, called Model53e, featuring a leading-edge slat and adjustable trailing-edge flaps. The model is studied for a Reynolds number of \(Re=1.0 \times 10^6\) and high angles of attack. For the experimental setup, unsteady deformation analyses are performed using a photogrammetry setup. Additionally, a comparison with acceleration sensors is conducted to assess the capabilities of photogrammetric measurements. The experimental findings are used to validate aeroelastic simulations. The results show that the mean deformation of the wing significantly influences the surface pressure distribution, while the structural vibration magnitude is small and thus negligible for simulations.