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Prism layers at airfoil using shappyHexMesh

Posted October 20, 2014 at 06:58 by skeptik (CFD notes)

Hard work with stupid snappyHexMeshDict bruteforcing and i have a result

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Old

2 blade model NACA23015

Posted October 1, 2014 at 06:49 by skeptik (CFD notes)

Seems to be true,
My polyMesh test.

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TSAGI HERITAGE, NACA23012, M=0.6, alpha = 3 grad

Posted May 23, 2014 at 04:07 by skeptik (CFD notes)

Code:
#NACA 23012 exp. results alpha = 3°00' M=0.6
# Cp=(Pfoil - Pinfinity)/q; q = rho*U^2/2
#columns
#    x    Cp
#Upper
1    -0.200
2.5    -0.710    
5    -1.070
7.5    -1.270
10    -1.400
15    -1.345
20    -0.930
25    -0.795
30    -0.700
35    -0.610
40    -0.540
45    -0.475
50    -0.410
55    -0.350
60    -0.280
65    -0.220
70    -0.170
75    -0.130
80
...
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TSAGI HERITAGE, NACA23012, M=0.642, alpha = 1.67 grad

Posted May 20, 2014 at 04:11 by skeptik (CFD notes)

Code:
#NACA 23012 exp. results alpha = 1°40' M=0.64
# Cp=(Pfoil - Pinfinity)/q; q = rho*U^2/2
#columns
#    x    Cp
#Upper
1    0.400
2.5    -0.380    
5    -0.780
7.5    -1.000
10    -1.160
15    -1.300
20    -0.925
25    -0.750
30    -0.640
35    -0.580
40    -0.520
45    -0.455
50    -0.395
55    -0.340
60    -0.280
65    -0.220
70    -0.165
75    -0.115
80
...
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TSAGI HERITAGE, NACA23012, M=0.62, alpha = 0.17 grad

Posted May 16, 2014 at 02:34 by skeptik (CFD notes)

Code:
#NACA 23012 exp. results alpha = 0°10' M=0.62
# Cp=(Pfoil - Pinfinity)/q; q = rho*U^2/2
#columns
#    x    Cp
#Upper
0.648850002166  0.594351799714
1.00056308745  0.206219950622
3.45475808897  -0.457764109672
6.14544982025  -0.727560965045
8.6724130463  -0.885641269979
10.7411097154  -0.932091653311
13.3867544506  -0.89601940486
20.5760817776  -0.711551955646
24.6874864642  -0.627989777797
32.0344782778  -0.51406419197
...
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