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

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NACA0021 airfoil beyond stall • NACA0021 at 60°AoA, experiment by Swalwell at al., 2003 • Re = 2.7·10 5 , low Mach number, domain span-size 4 chords • O-grid: courtesy of NTS, Russia, 1.9 million elements, y + ≈ 1 Contours of L / ∆ ∈ [0, 0.5] Isosurface of Q = Ω 2 - S 2 © 2007 ANSYS, Inc. All rights reserved. 12 ANSYS, Inc. Proprietary
NACA0021 airfoil beyond stall • Mean values and PSD spectra of forces SST-SAS Experiment -Cp 2.5 2 1.5 1 0.5 0 -0.5 -1 -1.5 Mean pressure -0.1 0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1 1.1 x/c C L 0.915 0.931 SST-SAS Experiment C D 1.484 1.517 © 2007 ANSYS, Inc. All rights reserved. 13 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: SST-SAS turbulence model • Decay
Page 15 and 16: Delta wing • Hybrid unstructured
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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