AG36 (ag36-il)
AG36 - Drela AG36 airfoil
| Details | Dat file | Parser | |
|
(ag36-il) AG36 Drela AG36 airfoil Max thickness 8.2% at 27.9% chord. Max camber 2.3% at 37% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
AG36
1.000003 0.002671
0.993991 0.003641
0.983912 0.005266
0.972030 0.007181
0.959208 0.009247
0.946050 0.011369
0.932962 0.013479
0.920159 0.015543
0.907668 0.017556
0.895474 0.019522
0.883699 0.021360
0.870771 0.023227
0.857975 0.025012
0.845188 0.026795
0.832275 0.028596
0.819232 0.030415
0.806149 0.032241
0.793050 0.034067
0.779976 0.035891
0.766906 0.037713
0.753833 0.039537
0.740771 0.041359
0.727741 0.043176
0.714758 0.044986
0.701919 0.046776
0.689366 0.048527
0.677377 0.050200
0.664649 0.051879
0.652447 0.053315
0.640918 0.054568
0.628145 0.055906
0.615243 0.057187
0.602241 0.058477
0.589040 0.059787
0.575726 0.061108
0.562405 0.062429
0.549108 0.063749
0.535834 0.065066
0.522613 0.066377
0.509419 0.067687
0.496304 0.068989
0.483304 0.070278
0.470656 0.071534
0.458359 0.072753
0.445894 0.073861
0.433427 0.074908
0.420872 0.075896
0.408284 0.076816
0.395608 0.077673
0.382819 0.078458
0.369887 0.079171
0.356838 0.079807
0.343750 0.080355
0.330663 0.080811
0.317617 0.081175
0.304632 0.081461
0.291705 0.081662
0.278830 0.081769
0.265979 0.081778
0.253138 0.081683
0.240295 0.081478
0.227476 0.081157
0.214697 0.080715
0.201993 0.080143
0.189391 0.079442
0.176920 0.078603
0.164596 0.077626
0.152422 0.076506
0.140378 0.075232
0.128500 0.073800
0.116809 0.072199
0.105313 0.070415
0.094012 0.068433
0.082843 0.066214
0.071888 0.063743
0.061341 0.061036
0.051360 0.058108
0.042120 0.055009
0.033853 0.051846
0.026739 0.048740
0.020859 0.045811
0.016127 0.043144
0.012360 0.040758
0.009362 0.038628
0.006964 0.036710
0.005060 0.034982
0.003534 0.033393
0.002309 0.031907
0.001353 0.030504
0.000648 0.029159
0.000194 0.027848
0.000000 0.026309
0.000132 0.024817
0.000499 0.023544
0.001172 0.022228
0.002191 0.020915
0.003558 0.019663
0.005312 0.018465
0.007482 0.017306
0.010121 0.016172
0.013360 0.015034
0.017387 0.013858
0.022470 0.012613
0.028917 0.011289
0.036947 0.009926
0.046502 0.008580
0.057245 0.007335
0.068770 0.006220
0.080769 0.005246
0.093063 0.004396
0.105547 0.003663
0.118159 0.003025
0.130865 0.002475
0.143646 0.002005
0.156485 0.001599
0.169372 0.001259
0.182302 0.000971
0.195271 0.000730
0.208276 0.000533
0.221309 0.000373
0.234368 0.000243
0.247445 0.000144
0.260548 0.000069
0.273668 0.000023
0.286811 0.000010
0.299969 0.000001
0.313145 -0.000001
0.326347 -0.000001
0.339561 -0.000001
0.352775 -0.000003
0.365989 -0.000002
0.379209 -0.000002
0.392435 -0.000003
0.405661 -0.000003
0.418885 -0.000001
0.432102 -0.000003
0.445323 -0.000002
0.458549 -0.000002
0.471776 -0.000003
0.484996 -0.000002
0.498215 -0.000003
0.511436 -0.000003
0.524664 -0.000002
0.537889 -0.000003
0.551110 -0.000003
0.564324 -0.000002
0.577539 -0.000003
0.590761 -0.000003
0.603980 -0.000002
0.617200 -0.000002
0.630423 -0.000003
0.643651 -0.000002
0.656876 -0.000002
0.670097 -0.000001
0.683316 -0.000002
0.696538 -0.000001
0.709765 -0.000002
0.722989 -0.000001
0.736210 -0.000003
0.749428 -0.000002
0.762651 -0.000001
0.775880 -0.000001
0.789103 -0.000001
0.802324 -0.000001
0.815536 -0.000001
0.828754 -0.000001
0.841972 -0.000001
0.855190 -0.000001
0.868401 -0.000001
0.881611 -0.000001
0.894828 -0.000001
0.908049 0.000000
0.921271 -0.000001
0.934482 0.000000
0.947646 0.000000
0.960667 0.000000
0.973288 0.000000
0.984906 0.000000
0.994731 0.000000
1.000000 0.000001
|
Dat file parser warnings
|
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for AG36 (ag36-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ag36-il | 50,000 | 9 | 32.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag36-il | 50,000 | 5 | 36.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag36-il | 100,000 | 9 | 50.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag36-il | 100,000 | 5 | 51 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag36-il | 200,000 | 9 | 67.5 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag36-il | 200,000 | 5 | 64.3 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag36-il | 500,000 | 9 | 88.9 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag36-il | 500,000 | 5 | 81 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag36-il | 1,000,000 | 9 | 103 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag36-il | 1,000,000 | 5 | 93 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||