AG12 (ag12-il)
AG12 - Drela AG12 airfoil
| Details | Dat file | Parser | |
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(ag12-il) AG12 Drela AG12 airfoil Max thickness 6.2% at 20.8% chord. Max camber 1.8% at 42.8% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
AG12
1.000000 0.000471
0.994142 0.001042
0.982204 0.002222
0.968696 0.003522
0.954910 0.004823
0.941098 0.006097
0.927274 0.007345
0.913441 0.008575
0.899593 0.009787
0.885734 0.010985
0.871861 0.012172
0.857979 0.013351
0.844090 0.014522
0.830201 0.015686
0.816312 0.016845
0.802424 0.017996
0.788539 0.019141
0.774659 0.020278
0.760778 0.021407
0.746901 0.022526
0.733027 0.023634
0.719152 0.024731
0.705280 0.025817
0.691409 0.026889
0.677538 0.027948
0.663670 0.028994
0.649803 0.030024
0.635935 0.031038
0.622068 0.032036
0.608205 0.033016
0.594342 0.033978
0.580478 0.034920
0.566619 0.035841
0.552761 0.036741
0.538905 0.037617
0.525049 0.038470
0.511197 0.039296
0.497347 0.040096
0.483500 0.040866
0.469656 0.041607
0.455816 0.042313
0.441978 0.042986
0.428143 0.043622
0.414316 0.044218
0.400492 0.044774
0.386673 0.045285
0.372861 0.045751
0.359053 0.046165
0.345250 0.046528
0.331461 0.046836
0.317683 0.047081
0.303912 0.047262
0.290156 0.047375
0.276418 0.047413
0.262691 0.047371
0.248985 0.047243
0.235302 0.047024
0.221638 0.046704
0.208004 0.046279
0.194402 0.045737
0.180830 0.045066
0.167304 0.044260
0.153819 0.043301
0.140392 0.042180
0.127049 0.040877
0.113793 0.039371
0.100663 0.037640
0.087677 0.035653
0.074897 0.033377
0.062374 0.030770
0.050223 0.027789
0.038618 0.024400
0.027917 0.020611
0.018756 0.016601
0.011861 0.012819
0.007244 0.009642
0.004260 0.007074
0.002309 0.004947
0.001028 0.003119
0.000261 0.001485
0.000000 -0.000011
0.000299 -0.001481
0.001263 -0.002904
0.002871 -0.004229
0.005195 -0.005565
0.008563 -0.007032
0.013654 -0.008722
0.021338 -0.010619
0.031664 -0.012466
0.043571 -0.013982
0.056254 -0.015147
0.069286 -0.016003
0.082543 -0.016609
0.095952 -0.017016
0.109468 -0.017263
0.123058 -0.017375
0.136704 -0.017378
0.150385 -0.017283
0.164098 -0.017105
0.177834 -0.016851
0.191595 -0.016531
0.205382 -0.016156
0.219178 -0.015730
0.232992 -0.015261
0.246823 -0.014753
0.260663 -0.014213
0.274519 -0.013643
0.288396 -0.013052
0.302276 -0.012444
0.316162 -0.011821
0.330060 -0.011187
0.343964 -0.010546
0.357874 -0.009899
0.371793 -0.009250
0.385719 -0.008601
0.399644 -0.007955
0.413564 -0.007312
0.427475 -0.006678
0.441384 -0.006050
0.455289 -0.005434
0.469185 -0.004829
0.483074 -0.004240
0.496967 -0.003667
0.510856 -0.003112
0.524739 -0.002575
0.538618 -0.002060
0.552501 -0.001566
0.566379 -0.001094
0.580251 -0.000648
0.594125 -0.000227
0.608000 0.000167
0.621871 0.000536
0.635737 0.000876
0.649609 0.001189
0.663478 0.001474
0.677342 0.001730
0.691207 0.001956
0.705074 0.002153
0.718938 0.002321
0.732801 0.002458
0.746669 0.002565
0.760534 0.002643
0.774396 0.002689
0.788262 0.002707
0.802128 0.002695
0.815988 0.002653
0.829854 0.002581
0.843721 0.002481
0.857585 0.002351
0.871458 0.002194
0.885322 0.002011
0.899184 0.001798
0.913057 0.001557
0.926935 0.001293
0.940803 0.001006
0.954669 0.000690
0.968513 0.000352
0.982113 -0.000002
0.994133 -0.000323
1.000000 -0.000471
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Polars for AG12 (ag12-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ag12-il | 50,000 | 9 | 33.2 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag12-il | 50,000 | 5 | 35.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag12-il | 100,000 | 9 | 47.1 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag12-il | 100,000 | 5 | 47 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag12-il | 200,000 | 9 | 61.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag12-il | 200,000 | 5 | 58.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag12-il | 500,000 | 9 | 79.6 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag12-il | 500,000 | 5 | 74.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag12-il | 1,000,000 | 9 | 92.6 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag12-il | 1,000,000 | 5 | 87.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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