AG04 (ag04-il)
AG04 - Drela AG04 airfoil
| Details | Dat file | Parser | |
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(ag04-il) AG04 Drela AG04 airfoil Max thickness 6.4% at 22.5% chord. Max camber 1.7% at 41.5% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
AG04
0.999999 0.000670
0.994870 0.001167
0.984963 0.002107
0.973288 0.003174
0.960910 0.004278
0.948332 0.005403
0.935708 0.006542
0.923068 0.007688
0.910423 0.008838
0.897782 0.009989
0.885148 0.011139
0.872522 0.012283
0.859901 0.013420
0.847283 0.014552
0.834669 0.015674
0.822056 0.016786
0.809443 0.017889
0.796831 0.018980
0.784217 0.020061
0.771601 0.021132
0.758985 0.022192
0.746366 0.023242
0.733743 0.024281
0.721120 0.025311
0.708496 0.026332
0.695872 0.027342
0.683249 0.028342
0.670629 0.029330
0.658010 0.030306
0.645393 0.031267
0.632779 0.032216
0.620167 0.033147
0.607557 0.034064
0.594950 0.034963
0.582346 0.035844
0.569745 0.036705
0.557147 0.037545
0.544551 0.038364
0.531959 0.039158
0.519370 0.039929
0.506783 0.040673
0.494200 0.041391
0.481620 0.042082
0.469042 0.042741
0.456467 0.043370
0.443895 0.043967
0.431325 0.044532
0.418758 0.045062
0.406195 0.045558
0.393636 0.046016
0.381082 0.046436
0.368533 0.046816
0.355990 0.047155
0.343456 0.047449
0.330929 0.047699
0.318413 0.047899
0.305908 0.048048
0.293416 0.048143
0.280938 0.048180
0.268477 0.048156
0.256036 0.048067
0.243615 0.047906
0.231219 0.047672
0.218852 0.047357
0.206516 0.046956
0.194219 0.046460
0.181965 0.045864
0.169762 0.045159
0.157618 0.044335
0.145544 0.043381
0.133552 0.042286
0.121659 0.041034
0.109883 0.039614
0.098252 0.038005
0.086796 0.036191
0.075561 0.034151
0.064602 0.031864
0.054003 0.029317
0.043899 0.026506
0.034516 0.023466
0.026187 0.020297
0.019250 0.017178
0.013839 0.014300
0.009798 0.011763
0.006815 0.009556
0.004604 0.007625
0.002958 0.005908
0.001739 0.004355
0.000861 0.002932
0.000285 0.001613
0.000018 0.000382
0.000085 -0.000805
0.000554 -0.001985
0.001456 -0.003123
0.002756 -0.004215
0.004455 -0.005308
0.006633 -0.006445
0.009447 -0.007655
0.013152 -0.008964
0.018112 -0.010393
0.024689 -0.011906
0.032994 -0.013392
0.042729 -0.014711
0.053413 -0.015788
0.064674 -0.016627
0.076299 -0.017257
0.088178 -0.017709
0.100238 -0.018017
0.112430 -0.018202
0.124717 -0.018284
0.137072 -0.018277
0.149484 -0.018198
0.161943 -0.018058
0.174443 -0.017866
0.186982 -0.017630
0.199555 -0.017356
0.212160 -0.017050
0.224791 -0.016716
0.237445 -0.016358
0.250118 -0.015977
0.262807 -0.015581
0.275506 -0.015166
0.288211 -0.014738
0.300918 -0.014299
0.313621 -0.013852
0.326319 -0.013398
0.339010 -0.012941
0.351696 -0.012481
0.364379 -0.012021
0.377057 -0.011562
0.389731 -0.011106
0.402402 -0.010652
0.415069 -0.010206
0.427732 -0.009763
0.440393 -0.009328
0.453052 -0.008901
0.465714 -0.008484
0.478381 -0.008076
0.491052 -0.007677
0.503725 -0.007290
0.516399 -0.006917
0.529072 -0.006554
0.541743 -0.006205
0.554416 -0.005866
0.567087 -0.005540
0.579758 -0.005227
0.592428 -0.004930
0.605099 -0.004643
0.617771 -0.004371
0.630444 -0.004115
0.643115 -0.003870
0.655786 -0.003641
0.668459 -0.003428
0.681132 -0.003228
0.693806 -0.003044
0.706482 -0.002875
0.719160 -0.002720
0.731838 -0.002579
0.744517 -0.002449
0.757198 -0.002333
0.769881 -0.002225
0.782566 -0.002127
0.795254 -0.002035
0.807944 -0.001951
0.820638 -0.001872
0.833336 -0.001792
0.846040 -0.001721
0.858750 -0.001652
0.871466 -0.001585
0.884186 -0.001519
0.896901 -0.001451
0.909612 -0.001377
0.922323 -0.001294
0.935033 -0.001202
0.947738 -0.001104
0.960407 -0.001010
0.972913 -0.000907
0.984778 -0.000805
0.994829 -0.000713
1.000001 -0.000670
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Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
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Polars for AG04 (ag04-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ag04-il | 50,000 | 9 | 32 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag04-il | 50,000 | 5 | 33.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag04-il | 100,000 | 9 | 45.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag04-il | 100,000 | 5 | 45.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag04-il | 200,000 | 9 | 58.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag04-il | 200,000 | 5 | 57 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag04-il | 500,000 | 9 | 76.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag04-il | 500,000 | 5 | 72.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag04-il | 1,000,000 | 9 | 90 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag04-il | 1,000,000 | 5 | 85 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||