In this paper, the conversion of a T-tail aircraft model to Vee-tail has investigated. Analytical research was carried out for the geometry of the tail as well as for the selection of the airfoil of the model, which specifically is NACA 64A010. Moreover, a 2-D computational analysis was set, for the airfoil investigation at Reynolds 130.000 and a 3-D computational analysis was performed for the Vee-tail for different angles of attack and side-slip, using the turbulent models Spalart-Allmaras, Realizable k-ε and SST k-ω. The analysis concludes that the experimental, theoretical and analytical results are in agreement with the computational process. For the Vee-tail, the analysis shows that the CL follows a linear variation in relation with the angle of attack up to 7° whereas the results with the turbulent models begin to deviate. In addition, for the CD relative to the angle of attack, a convergence among the various turbulent models as well as with the theoretical results was observed. With the increase of the sideslip angle, loss of the aerodynamic performance of the Vee-tail model is observed. At 8°, the CD increases 30% while the CL decreases 9%. For the 12°, the CD increases dramatically up to 76% and at 24°, the aerodynamic performance is completely reduced to zero.