Development and Application of SST-SAS Turbulence Model in the ...

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Delta wing • Sweep angle 76°, experiment by Laschka et al., 1995 • AoA = 35°, Re = 1.07·10 6 , low Mach number © 2007 ANSYS, Inc. All rights reserved. 14 ANSYS, Inc. Proprietary
Delta wing • Hybrid unstructured grid, 50 million elements, y + ≈ 0.5 – Courtesy of EADS Deutschland GmbH, Military Air Systems © 2007 ANSYS, Inc. All rights reserved. 15 ANSYS, Inc. Proprietary
Page 1 and 2: Development and Application of SST-
Page 3 and 4: SAS concept • URANS: unphysical s
Page 5 and 6: SAS concept. 2-eq RANS models • k
Page 7 and 8: SAS concept. SAS and RANS • ⎛ 2
Page 9 and 10: SAS concept definition • SAS: 2 n
Page 11 and 12: SST-SAS turbulence model • Decay
Page 13: NACA0021 airfoil beyond stall • M
Page 17 and 18: Full aircraft configuration • Del
Page 19 and 20: Full aircraft configuration • Res
Page 21 and 22: 3-D acoustic cavity • M219 test c
Page 23: Other DESIDER tests simulated • B

Development and Application of SST-SAS Turbulence Model in the ...

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