Flutter simulations of a T-tail configuration using non-linear aerodynamics

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Flutter simulations of a T-tail configuration using non-linear aerodynamics

Arizono, H. / Kheirandish, H.R. / Nakamichi, J.

A numerical flutter simulation of a T-tail configuration in the transonic region is presented. A code for aeroelastic simulations based on the multi-block and overset grid concept was developed and has been applied to a T-tail configuration. Flutter simulations are performed at Mach numbers in the range 0.70-0.95, and the obtained results correspond to experimental results. The effect of varying the angle of attack on the flutter boundary is also presented. The present study was conducted in order to support the development of an advanced tool for the estimation of the flutter boundary, especially in the transonic region. The motion of the vertical tailplane dominates that of the horizontal tailplane. The present tool is shown to be a necessary and powerful for estimating flutter speed, especially in the transonic regime. For further investigation of the characteristics of T-tail flutter, a viscous flow model shall be used for detailing not only the behaviours of the shock wave but also the flow interactions near the intersection of the vertical tailplane and the horizontal tailplane. Unfortunately, the stiffness of the vertical tailplane from the wind tunnel model is too large to observe the classical T-tail flutter with dominant vertical tailplane lateral bending and antisymmetric natural modes of the horizontal tailplane.