AERODYNAMICS AND STATIC STABILITY INVESTIGATION OF A V - TAIL LAYOUT USING CFD METHODS AND VARIOUS TURBULENCE MODELS

In this paper, the conversion of a T - tail aircraft model to V ee - 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 com putational analysis was set, for the airfoil investigation at Reynolds 130.000 and a 3 - D computational analysis was performed for the V ee - tail for different angles of attack and side - slip, using the turbulent models Spalart - Allmaras, Realizable k - ε and SS T k - ω. The analysis concludes that the experimental, theoretical and analytical results are in agreement with the co mputational process. For the Vee - tail , the analysis shows that the C L follows a linear variation in relation w ith the angle of attack up to 7 ° whereas the results with the turbulent models begin to deviate. In addition, for the C D relative to the angle of attack, a convergence among the various turbulent models as well as with the theoretical results was observed. With the incr ease of the si de slip angle, loss of the aerodynamic performance of the V ee - tail model is observed. At 8 ° , the C D increases 30% wh ile the C L decreases 9%. For the 12 ° , the C D increases dramatically up to 76% and at 24 ° , the aerodynamic performance is completely reduced t o zero.