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AG04 (ag04-il)

AG04 - Drela AG04 airfoil


Airfoil ag04-il
Details Dat file Parser  
(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
Dat file parser warnings
  • Line 181 - X value too large but included: 1.000001 -0.000670
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Lednicer format dat file
Selig format dat file

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Polars for AG04 (ag04-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   ag04-il50,000932 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   ag04-il50,000533.9 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   ag04-il100,000945.4 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ag04-il100,000545.3 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   ag04-il200,000958.9 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ag04-il200,000557 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   ag04-il500,000976.8 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   ag04-il500,000572.8 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   ag04-il1,000,000990 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   ag04-il1,000,000585 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
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