Elsa Bréus, Nicolas Forestier, Zdenek Johan, Eric Garrigues

DOI Number: N/A

Conference number: IFASD-2024-104

Flutter computations on a T-tail aircraft hold challenges as flutter behavior is significantly driven by specific aerodynamic phenomena. Interactions between tail surfaces have
to be computed correctly to predict flutter accurately. Developments were performed at DASSAULT AVIATION to improve in-house solvers for these specific configurations. To
validate numerical tools, some reference experimental data are required. To do so, a wind tunnel test mock-up has been designed and manufactured in the frame of CleanSky2 project in cooperation between DASSAULT AVIATION, ONERA and RUAG. This mock-up was tested in 2016 for U-tail configurations [1]. A second wind tunnel test campaign took place in 2022 for T-tail configurations in ONERA S2MA pressurized wind tunnel. Flutter curves have been measured up to the flutter point thanks to an efficient safety system that allowed reaching flutter boundary numerous times without structural damage. The tests, conducted up to Mach 0.925, have shown good repeatability leading to a high confidence in the measurements. Configurations tested consisted in several incidence settings of the horizontal tail plane to cover various lift forces and a dihedral effect. Both effects are of prime importance when computing flutter of a T-tail configuration. These effects therefore call for the need of validation of their numerical predictions. This paper presents correlations between experimental data and numerical computations.

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In Categories: 1. IFASD 2024, 1.Events, Steady/Unsteady Aerodynamics
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