In this diploma thesis we deal with the preliminary design of an aircraft horizontal stabilizer, in which its aeroelastic properties, namely the critical speeds of torsional divergence and flutter, are placed in the foreground. The aim of the work is to develop and apply a computational tool with which it is possible to evaluate the influence of geometric and material parameters of the stabilizer on these aeroelastic boundary speeds, on mass, material cost and an estimate of the effect on fuel consumption, and on longitudinal static and dynamic stability, which we treat as a constraint. The model combines basic aerodynamic relations, a simplified structural description of the tail box and a parametric treatment of materials, airfoils and planform geometry. The analysis is carried out on a reference transport aircraft, while the results are presented in the form of tables, diagrams and influence matrices. Special emphasis is placed on comparing trends between individual configurations, since the developed model represents a preliminary engineering tool and does not replace detailed certification analysis using FEM, CFD or experimental testing. The results make it possible to identify the main influential parameters and serve as guidelines for the initial design of horizontal tail surfaces.
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