AG37 (ag37-il)
AG37 - Drela AG37 airfoil
| Details | Dat file | Parser | |
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(ag37-il) AG37 Drela AG37 airfoil Max thickness 7.7% at 26.5% chord. Max camber 2.1% at 35.5% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
AG37
1.000000 0.003508
0.993634 0.004540
0.983839 0.006128
0.972384 0.007984
0.960126 0.009970
0.947509 0.012015
0.934838 0.014069
0.922272 0.016105
0.909672 0.018147
0.897163 0.020174
0.884502 0.022136
0.872236 0.023744
0.859132 0.025363
0.845998 0.026986
0.832762 0.028622
0.819330 0.030281
0.805796 0.031954
0.792287 0.033623
0.778764 0.035294
0.765277 0.036961
0.751736 0.038634
0.738244 0.040301
0.724795 0.041963
0.711419 0.043616
0.698229 0.045246
0.685362 0.046836
0.672702 0.048400
0.659989 0.049874
0.648296 0.051133
0.636014 0.052350
0.622979 0.053568
0.610109 0.054732
0.597124 0.055906
0.583924 0.057099
0.570608 0.058304
0.557288 0.059508
0.543987 0.060711
0.530692 0.061913
0.517439 0.063111
0.504203 0.064308
0.491039 0.065499
0.478020 0.066675
0.465306 0.067826
0.453088 0.068931
0.440823 0.069934
0.428638 0.070879
0.416395 0.071774
0.404233 0.072598
0.392113 0.073355
0.379952 0.074055
0.367557 0.074706
0.354881 0.075304
0.342042 0.075842
0.329120 0.076312
0.316188 0.076710
0.303310 0.077030
0.290456 0.077269
0.277633 0.077424
0.264786 0.077488
0.251944 0.077457
0.239030 0.077318
0.226008 0.077063
0.212844 0.076678
0.199532 0.076147
0.186403 0.075471
0.173367 0.074641
0.160427 0.073645
0.147589 0.072472
0.134778 0.071102
0.122032 0.069519
0.109366 0.067704
0.096850 0.065646
0.085381 0.063498
0.074326 0.061155
0.063754 0.058627
0.053804 0.055941
0.044531 0.053109
0.036013 0.050157
0.028389 0.047142
0.021830 0.044161
0.016458 0.041336
0.012225 0.038754
0.008994 0.036451
0.006578 0.034442
0.004804 0.032719
0.003498 0.031245
0.002484 0.029908
0.001659 0.028617
0.000975 0.027306
0.000462 0.026004
0.000097 0.024530
0.000005 0.023090
0.000139 0.021997
0.000479 0.020847
0.001101 0.019658
0.002090 0.018460
0.003442 0.017314
0.005164 0.016221
0.007326 0.015167
0.009992 0.014136
0.013260 0.013114
0.017315 0.012059
0.022425 0.010949
0.028894 0.009771
0.036949 0.008569
0.046522 0.007388
0.057281 0.006303
0.068822 0.005337
0.080832 0.004491
0.093131 0.003758
0.105621 0.003130
0.118238 0.002594
0.130947 0.002135
0.143732 0.001745
0.156572 0.001410
0.169460 0.001125
0.182388 0.000884
0.195358 0.000679
0.208361 0.000508
0.221395 0.000367
0.234451 0.000255
0.247531 0.000166
0.260630 0.000098
0.273751 0.000052
0.286893 0.000021
0.300050 0.000002
0.313224 -0.000009
0.326425 -0.000016
0.339638 -0.000016
0.352851 -0.000015
0.366065 -0.000015
0.379284 -0.000015
0.392508 -0.000016
0.405734 -0.000015
0.418957 -0.000013
0.432174 -0.000016
0.445391 -0.000014
0.458618 -0.000013
0.471843 -0.000014
0.485062 -0.000013
0.498279 -0.000013
0.511500 -0.000014
0.524726 -0.000012
0.537952 -0.000014
0.551171 -0.000014
0.564383 -0.000012
0.577598 -0.000013
0.590818 -0.000013
0.604037 -0.000011
0.617254 -0.000011
0.630479 -0.000011
0.643705 -0.000010
0.656928 -0.000010
0.670149 -0.000008
0.683367 -0.000010
0.696587 -0.000008
0.709814 -0.000009
0.723037 -0.000008
0.736256 -0.000010
0.749473 -0.000008
0.762697 -0.000008
0.775924 -0.000006
0.789146 -0.000006
0.802363 -0.000005
0.815577 -0.000005
0.828791 -0.000005
0.842011 -0.000004
0.855227 -0.000006
0.868438 -0.000006
0.881646 -0.000005
0.894863 -0.000005
0.908082 -0.000004
0.921304 -0.000003
0.934512 -0.000002
0.947676 -0.000001
0.960697 -0.000002
0.973318 -0.000002
0.984934 -0.000001
0.994759 -0.000001
1.000000 0.000000
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Polars for AG37 (ag37-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ag37-il | 50,000 | 9 | 32.9 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag37-il | 50,000 | 5 | 36.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag37-il | 100,000 | 9 | 49.3 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag37-il | 100,000 | 5 | 49.8 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag37-il | 200,000 | 9 | 65.3 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag37-il | 200,000 | 5 | 62.5 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag37-il | 500,000 | 9 | 85.2 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag37-il | 500,000 | 5 | 78.6 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag37-il | 1,000,000 | 9 | 98.9 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag37-il | 1,000,000 | 5 | 89.7 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||