Various approaches to control aeroelastic wing section with structural nonlinearity emerged in the last years. One of the approaches is based on the Tensor Product (TP) model transformation and the feasibility test of linear matrix inequalities (LMIs) under the Parallel Distributed Compensation framework. The main contribution of this paper is that it extends the previously established qLPV model of the aeroelastic wing section with nonlinear friction. It is proven that the extended model can be exactly described after TP type polytopic decomposition. The qLPV model of the aeroelastic wing section with Coulomb friction was transformed to TP type polytopic model form for which LMI based controller was designed. The designed controller is compared to controllers of other authors dealing with the same problem.