S7012 8.75% (s7012-il)
S7012 8.75% - Selig S7012 low Reynolds number airfoil
| Details | Dat file | Parser | |
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(s7012-il) S7012 8.75% Selig S7012 low Reynolds number airfoil Max thickness 8.7% at 27.7% chord. Max camber 1.7% at 38.1% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
S7012 8.75%
1.00000 0.00000
0.99819 0.00024
0.99294 0.00104
0.98451 0.00231
0.97296 0.00392
0.95833 0.00586
0.94077 0.00817
0.92044 0.01080
0.89749 0.01372
0.87210 0.01689
0.84445 0.02029
0.81474 0.02386
0.78318 0.02757
0.74999 0.03138
0.71540 0.03524
0.67965 0.03909
0.64298 0.04287
0.60563 0.04654
0.56785 0.05002
0.52988 0.05324
0.49193 0.05615
0.45426 0.05870
0.41710 0.06081
0.38070 0.06241
0.34520 0.06335
0.31071 0.06360
0.27741 0.06319
0.24543 0.06209
0.21486 0.06033
0.18590 0.05795
0.15865 0.05496
0.13326 0.05143
0.10983 0.04738
0.08846 0.04287
0.06926 0.03798
0.05229 0.03274
0.03759 0.02728
0.02525 0.02167
0.01528 0.01605
0.00773 0.01058
0.00266 0.00542
0.00007 0.00087
0.00069 -0.00278
0.00486 -0.00600
0.01208 -0.00918
0.02223 -0.01220
0.03523 -0.01495
0.05102 -0.01739
0.06952 -0.01950
0.09065 -0.02126
0.11428 -0.02265
0.14032 -0.02368
0.16861 -0.02436
0.19900 -0.02471
0.23131 -0.02474
0.26535 -0.02448
0.30091 -0.02396
0.33778 -0.02318
0.37572 -0.02220
0.41449 -0.02101
0.45383 -0.01965
0.49348 -0.01813
0.53316 -0.01644
0.57261 -0.01453
0.61171 -0.01227
0.65044 -0.00978
0.68859 -0.00732
0.72582 -0.00504
0.76182 -0.00300
0.79628 -0.00128
0.82889 0.00010
0.85936 0.00112
0.88743 0.00178
0.91283 0.00211
0.93533 0.00214
0.95473 0.00192
0.97084 0.00153
0.98352 0.00105
0.99266 0.00055
0.99816 0.00016
1.00000 0.00000
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Polars for S7012 8.75% (s7012-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s7012-il | 50,000 | 9 | 33.7 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s7012-il | 50,000 | 5 | 37.5 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s7012-il | 100,000 | 9 | 51.9 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s7012-il | 100,000 | 5 | 52.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s7012-il | 200,000 | 9 | 70.3 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s7012-il | 200,000 | 5 | 67.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s7012-il | 500,000 | 9 | 94.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s7012-il | 500,000 | 5 | 85.7 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s7012-il | 1,000,000 | 9 | 110.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s7012-il | 1,000,000 | 5 | 97 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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