This is an aerodynamic reduced order model (ROM) for Matlab/Simulink. It is applied to the scaled-up (x20) OAT15A airfoil, predicting the incremental lift of an arbitrary dynamic aileron deflection at Mach 0.73. The data contains the model and inputs to reproduce Figure 3.10 from the following PhD Dissertation: "Lancelot, P. M. G. J. (2023). Transonic Wing and Control Surface Loads Modelling for Aeroservoelastic Analysis. https://doi.org/10.4233/uuid:e37566e8-cb46-4f90-863d-9cfe0b634507"