Maximum lift predictions of a realistic commercial aircraft in landing configuration

Within task three “Numerical Simulations” in the project “HINVA - High Lift INflight Validation” extensive numerical verification studies based on a CAD model of DLR’s A320232 "Advanced Technology Research Aircraft" in landing configuration are carried out. Therein special attention is paid to the effect of certain geometric features of the high-lift system, such as slat tracks, de-icing pipe etc. Also the empennage and a model of both the operational engine and a through flow nacelle are included in the geometry. The numerical simulations are carried out using two different sets of flow solver settings. The first based on the Spallart-Allmaras turbulence model represents DLR’s current best-practice. The second set follows a high-precision approach based on a differential Reynolds stress turbulence model. In this paper the structure of the task is presented along with results of initial numerical simulations assessing the influence of the slat tracks, the de-icing pipe and the TFN in comparison to the operational engine.

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