Advanced Turbulence Modelling and Stress Analysis for the DLR-F6 Configuration

The current DLR Computational Fluid Dynamics validation activities in the framework of the AIAA Drag Prediction Workshop are presented. Since the second workshop in 2003 advanced turbulence models have been integrated in the Reynolds-averaged Navier-Stokes solver FLOWer. The hybrid SSG/LRR-omega differential Reynolds stress turbulence model is presented, combining the Launder-Reece-Rodi (LRR) model near walls with the Speziale-Sarkar-Gatski(SSG) model further apart by applying Menter's blending function F_1. Menter's baseline omega-equation is exploited for supplying the length scale. The SSG/LRR-omega model is applied to the DLR-F6 aircraft configuration. Results are presented for a target lift computation at C_L = 0.500 and for lift, drag and moment coefficients in a range of incidence from -3 to 1.5 degrees. In addition to the validation activities the possibility of anew wind tunnel testing of the DLR-F6 was investigated. Because a test at a higher Reynolds-number is of interest the mechanical strength of the model was analysed using the Finite-Element-Method software ANSYS.

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