The aim of this paper is to present a new method to predict aircraft directional characteristics. The proposed approach is completely CFD based and it has been developed with more than 300 simulations of complete and partial aircraft configurations. The method accounts for mutual aerodynamic interference effects among components. First, the isolated vertical tailplane and fuselage yawing moment coefficients are calculated. Then, correction factors are applied to take into account for aircraft components (fuselage, wing, vertical and horizontal tailplanes). The corrected yawing moment coefficients represent the contributions of vertical tailplane and fuselage to aircraft directional stability, including the aerodynamic interference among all aircraft components. Finally, the method is tested and compared to typical semi-empirical approaches (USAF DATCOM, ESDU).
Aircraft Directional Stability Prediction method by CFD / DELLA VECCHIA, Pierluigi; Nicolosi, Fabrizio; Ciliberti, Danilo. - Unico:(2015), pp. 1-12. (Intervento presentato al convegno 33rd AIAA Applied Aerodynamic Conference, AIAA Aviation Conference, 22-26 June, 2015 tenutosi a Dallas (Texas, USA) nel 22-26 June, 2015) [10.2514/6.2015-2255].
Aircraft Directional Stability Prediction method by CFD
DELLA VECCHIA, PIERLUIGI;NICOLOSI, FABRIZIO;CILIBERTI, DANILO
2015
Abstract
The aim of this paper is to present a new method to predict aircraft directional characteristics. The proposed approach is completely CFD based and it has been developed with more than 300 simulations of complete and partial aircraft configurations. The method accounts for mutual aerodynamic interference effects among components. First, the isolated vertical tailplane and fuselage yawing moment coefficients are calculated. Then, correction factors are applied to take into account for aircraft components (fuselage, wing, vertical and horizontal tailplanes). The corrected yawing moment coefficients represent the contributions of vertical tailplane and fuselage to aircraft directional stability, including the aerodynamic interference among all aircraft components. Finally, the method is tested and compared to typical semi-empirical approaches (USAF DATCOM, ESDU).File | Dimensione | Formato | |
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