A study was conducted to demonstrate aeroelastic wing section control via relaxed tensor product model transformation framework. The investigations focused on the three-degree-of-freedom (3-DOF) nonlinear aeroelastic test apparatus (NATA) model. The study also revisited the parallel distributed compensation (PDC) framework-based control solution of the 3-DOF NATA model in the case where the model was extended to incorporate friction. It presented a new general theoretical control design framework based on tensor product (TP) model transformation. The proposed framework was capable of a significant complexity reduction of quasi-linear parameter-varying (QLPV) models, including numerical and theoretical for linear matrix inequality (LMI)-based control design. The proposed control design framework was applied for active stabilization of the 3-DOF aeroelastic wing section as an extension of the design method.