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AG13 (ag13-il)

AG13 - Drela AG13 airfoil


Airfoil ag13-il
Details Dat file Parser  
(ag13-il) AG13
Drela AG13 airfoil
Max thickness 5.8% at 21.3% chord.
Max camber 2% at 41.8% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
AG13
     1.000000    0.000474
     0.994186    0.001043
     0.982196    0.002244
     0.968716    0.003561
     0.955020    0.004876
     0.941309    0.006158
     0.927567    0.007418
     0.913811    0.008664
     0.900051    0.009897
     0.886293    0.011116
     0.872535    0.012319
     0.858779    0.013507
     0.845019    0.014679
     0.831252    0.015837
     0.817483    0.016982
     0.803711    0.018116
     0.789935    0.019238
     0.776159    0.020351
     0.762383    0.021452
     0.748606    0.022541
     0.734830    0.023619
     0.721054    0.024685
     0.707276    0.025738
     0.693501    0.026778
     0.679727    0.027805
     0.665950    0.028817
     0.652176    0.029815
     0.638404    0.030796
     0.624631    0.031762
     0.610859    0.032709
     0.597088    0.033639
     0.583318    0.034549
     0.569550    0.035439
     0.555783    0.036308
     0.542018    0.037154
     0.528252    0.037977
     0.514490    0.038775
     0.500730    0.039547
     0.486972    0.040290
     0.473217    0.041006
     0.459464    0.041689
     0.445715    0.042339
     0.431970    0.042953
     0.418228    0.043530
     0.404492    0.044068
     0.390758    0.044562
     0.377031    0.045012
     0.363309    0.045415
     0.349594    0.045767
     0.335884    0.046065
     0.322183    0.046306
     0.308490    0.046486
     0.294806    0.046602
     0.281134    0.046648
     0.267472    0.046621
     0.253824    0.046516
     0.240191    0.046327
     0.226577    0.046050
     0.212982    0.045675
     0.199417    0.045196
     0.185886    0.044602
     0.172391    0.043881
     0.158943    0.043021
     0.145547    0.042008
     0.132215    0.040825
     0.118965    0.039452
     0.105812    0.037868
     0.092789    0.036047
     0.079938    0.033954
     0.067311    0.031549
     0.054993    0.028792
     0.043131    0.025630
     0.031968    0.022034
     0.021975    0.018057
     0.013919    0.014011
     0.008322    0.010434
     0.004775    0.007551
     0.002545    0.005228
     0.001129    0.003287
     0.000298    0.001590
     0.000000    0.000052
     0.000280   -0.001424
     0.001266   -0.002852
     0.002958   -0.004156
     0.005462   -0.005457
     0.009220   -0.006894
     0.015119   -0.008540
     0.023999   -0.010288
     0.035296   -0.011809
     0.047740   -0.012946
     0.060674   -0.013746
     0.073869   -0.014272
     0.087235   -0.014590
     0.100715   -0.014745
     0.114272   -0.014771
     0.127881   -0.014692
     0.141528   -0.014526
     0.155205   -0.014284
     0.168907   -0.013979
     0.182628   -0.013619
     0.196363   -0.013213
     0.210112   -0.012766
     0.223873   -0.012284
     0.237644   -0.011772
     0.251425   -0.011235
     0.265214   -0.010677
     0.279011   -0.010100
     0.292818   -0.009509
     0.306631   -0.008908
     0.320453   -0.008300
     0.334282   -0.007689
     0.348114   -0.007077
     0.361941   -0.006466
     0.375765   -0.005859
     0.389584   -0.005258
     0.403399   -0.004663
     0.417212   -0.004078
     0.431022   -0.003502
     0.444829   -0.002938
     0.458633   -0.002387
     0.472433   -0.001849
     0.486230   -0.001328
     0.500022   -0.000825
     0.513812   -0.000340
     0.527599    0.000123
     0.541382    0.000563
     0.555163    0.000979
     0.568942    0.001370
     0.582719    0.001734
     0.596494    0.002070
     0.610269    0.002377
     0.624044    0.002657
     0.637819    0.002908
     0.651594    0.003130
     0.665370    0.003323
     0.679145    0.003487
     0.692918    0.003622
     0.706694    0.003727
     0.720469    0.003803
     0.734246    0.003849
     0.748023    0.003866
     0.761799    0.003853
     0.775574    0.003811
     0.789353    0.003741
     0.803133    0.003642
     0.816912    0.003517
     0.830691    0.003363
     0.844473    0.003182
     0.858256    0.002975
     0.872041    0.002743
     0.885827    0.002486
     0.899612    0.002205
     0.913398    0.001898
     0.927190    0.001571
     0.940981    0.001222
     0.954766    0.000851
     0.968535    0.000458
     0.982113    0.000051
     0.994176   -0.000313
     1.00000    -0.000474
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Polars for AG13 (ag13-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   ag13-il50,000934.2 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   ag13-il50,000535.6 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   ag13-il100,000948.2 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   ag13-il100,000547.3 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   ag13-il200,000962.1 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   ag13-il200,000559 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ag13-il500,000979.9 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ag13-il500,000575.2 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ag13-il1,000,000992.9 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ag13-il1,000,000588.2 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
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