Modelling Aerodynamics Unsteady Loads on the Horizontal Tail Plane of a Civil Aircraft
During flight, emergency descent situations are part of those extreme conditions that can lead the empennage of an aircraft to vibrate. These vibrations are mainly due to the separated flow on the upper surface of the structure which increases the pressure fluctuations on the empennage, sometimes leading to buffeting. This situation can cause structural fatigue and can induce certification and design constraints on the structure. Hence, an accurate prediction of the unsteady loads is needed to take these forces into account in the early phase of the empennage design. This paper presents a new approach to accurately model the unsteady aerodynamic loads resulting from the interaction between the horizontal tail plane and the wing wake. The method is based upon the coherence method and is compared to the method developed by Soumillon , based upon the correlation method. The results obtained by this new model show good agreements with the experimental data.
R. Calderon et al., "Modelling Aerodynamics Unsteady Loads on the Horizontal Tail Plane of a Civil Aircraft", Applied Mechanics and Materials, Vol. 232, pp. 543-547, 2012