BAIL 2006 Book of Abstracts - Institut für Numerische und ...

TH. ALRUTZ, T. KNOPP: Near-wall grid adaptation for wall functions
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0.006 exp.
low-Re
y + (1) = 1
y + (1) = 20
0.004
c f
0.002
0
y + (1) = 40
y + (1) = 60
c f = 0
0 0.25 0.5 0.75 1
x/c
0.006 exp.
low-Re
y + (1) = 1
y + (1) = 20
0.004
c f
0.002
0
y + (1) = 40
y + (1) = 60
c f = 0
0 0.25 0.5 0.75 1
x/c
Figure 2: RAE2822 case 10 [5]: Prediction for skin friction coefficient�for Spalart-Allmaras-Edwards
model [3] without adaptation (left) and withÝ -adaptation of the prismatic near-wall grid (right).
c p
-4.2
-3.8
-3.4
-3
exp.
low-Re
y + (1) = 12
y + (1) = 24
y + (1) = 40
y + (1) = 80
0 0.05 0.1 0.15
x/c
Ý ÆÝ Ü×�Ô� Ü×�Ô�
SA-Edwards Menter SST
low-Re 33 0.771 0.866
1 33 0.770 0.866
4 28 0.755 0.863
7 26 0.759 0.868
12 24 0.761 0.861
24 21 0.787 0.861 (0.864)
50 19 (0.771) 0.881 (0.873)
70 17 (0.788) 0.903 (0.867)
Figure 3: A-airfoil [6]: Detail of pressure coefficientÔfor SST model [4] on adapted grid (left). Right:
Prediction of the separation point without adaptation and withÝ -adaptation (values in brackets).
[2] Th. Alrutz, “Hybrid grid adaptation in TAU”, In: MEGAFLOW - Numerical flow simulation for
aircraft design, Notes on Numerical Fluid Mechanics and Multidisciplinary Design. N. Kroll and
J.K. Fassbender, Eds., (2005).
[3] J.R. Edwards and S. Chandra, “Comparison of eddy viscosity-transport turbulence models for threedimensional,
shock separated flowfields”, AIAA Journal, 34, 756–763 (1996).
[4] F.R. Menter, “Zonal two equation�/�turbulence models for aerodynamic flows”, AIAA Paper
1993-2906, (1993).
[5] P. H. Cook, M. A. McDonald and M.C.P. Firmin, “Aerofoil RAE 2822 - Pressure distributions and
boundary layer and wake measurements”, AGARD Advisory Report AR-138, A6.1-A6.77 (1979).
[6] Ch. Gleyzes, “Opération décrochage - Résultats de la 2ème campagne d’essais à F2 – Mesures de
pression et vélocimétrie laser”, RT-DERAT 55/5004 DN, ONERA, (1989).
Speaker: ALRUTZ, TH 70 BAIL 2006
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