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AG14 (ag14-il)

AG14 - Drela AG14 airfoil


Airfoil ag14-il
Details Dat file Parser  
(ag14-il) AG14
Drela AG14 airfoil
Max thickness 5.4% at 19.9% chord.
Max camber 2% at 41.9% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
AG14
     1.000000    0.000478
     0.994163    0.001055
     0.982137    0.002278
     0.968690    0.003612
     0.955059    0.004933
     0.941417    0.006212
     0.927745    0.007460
     0.914064    0.008684
     0.900374    0.009882
     0.886671    0.011061
     0.872957    0.012225
     0.859240    0.013375
     0.845517    0.014514
     0.831794    0.015641
     0.818069    0.016757
     0.804341    0.017862
     0.790615    0.018957
     0.776887    0.020040
     0.763160    0.021112
     0.749432    0.022173
     0.735706    0.023219
     0.721979    0.024254
     0.708253    0.025274
     0.694527    0.026280
     0.680802    0.027271
     0.667077    0.028247
     0.653352    0.029206
     0.639628    0.030149
     0.625903    0.031074
     0.612179    0.031982
     0.598456    0.032872
     0.584732    0.033741
     0.571009    0.034592
     0.557286    0.035420
     0.543565    0.036229
     0.529844    0.037014
     0.516123    0.037777
     0.502405    0.038514
     0.488687    0.039228
     0.474972    0.039914
     0.461257    0.040572
     0.447546    0.041202
     0.433837    0.041799
     0.420130    0.042365
     0.406427    0.042895
     0.392729    0.043390
     0.379035    0.043843
     0.365347    0.044256
     0.351664    0.044624
     0.337988    0.044943
     0.324320    0.045211
     0.310660    0.045422
     0.297009    0.045575
     0.283370    0.045663
     0.269742    0.045683
     0.256127    0.045629
     0.242529    0.045494
     0.228948    0.045274
     0.215388    0.044959
     0.201855    0.044543
     0.188351    0.044014
     0.174882    0.043362
     0.161454    0.042577
     0.148076    0.041641
     0.134757    0.040539
     0.121509    0.039255
     0.108351    0.037766
     0.095308    0.036048
     0.082422    0.034067
     0.069741    0.031785
     0.057345    0.029157
     0.045367    0.026132
     0.034018    0.022662
     0.023704    0.018760
     0.015128    0.014652
     0.008995    0.010888
     0.005109    0.007828
     0.002704    0.005389
     0.001202    0.003381
     0.000323    0.001647
     0.000001    0.000099
     0.000271   -0.001386
     0.001281   -0.002806
     0.003035   -0.004061
     0.005650   -0.005271
     0.009630   -0.006579
     0.015964   -0.008033
     0.025442   -0.009472
     0.037184   -0.010613
     0.049858   -0.011373
     0.062925   -0.011822
     0.076214   -0.012038
     0.089637   -0.012080
     0.103143   -0.011986
     0.116711   -0.011785
     0.130326   -0.011498
     0.143975   -0.011143
     0.157650   -0.010734
     0.171348   -0.010280
     0.185063   -0.009791
     0.198792   -0.009274
     0.212536   -0.008735
     0.226289   -0.008180
     0.240052   -0.007614
     0.253822   -0.007038
     0.267597   -0.006459
     0.281378   -0.005876
     0.295159   -0.005294
     0.308937   -0.004713
     0.322711   -0.004137
     0.336480   -0.003566
     0.350246   -0.003002
     0.364008   -0.002449
     0.377766   -0.001905
     0.391520   -0.001375
     0.405271   -0.000860
     0.419018   -0.000361
     0.432762    0.000120
     0.446504    0.000580
     0.460245    0.001022
     0.473985    0.001441
     0.487723    0.001838
     0.501461    0.002212
     0.515198    0.002563
     0.528935    0.002892
     0.542672    0.003195
     0.556409    0.003475
     0.570147    0.003731
     0.583884    0.003962
     0.597622    0.004169
     0.611360    0.004352
     0.625099    0.004509
     0.638837    0.004643
     0.652577    0.004752
     0.666317    0.004837
     0.680057    0.004899
     0.693798    0.004935
     0.707538    0.004949
     0.721280    0.004939
     0.735021    0.004905
     0.748762    0.004847
     0.762503    0.004767
     0.776244    0.004662
     0.789983    0.004534
     0.803722    0.004381
     0.817460    0.004205
     0.831198    0.004003
     0.844934    0.003776
     0.858669    0.003525
     0.872403    0.003248
     0.886136    0.002946
     0.899868    0.002617
     0.913600    0.002264
     0.927331    0.001884
     0.941061    0.001479
     0.954791    0.001047
     0.968507    0.000592
     0.982058    0.000121
     0.994155   -0.000295
     1.000000   -0.000478
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Polars for AG14 (ag14-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   ag14-il50,000934.8 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   ag14-il50,000535.8 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   ag14-il100,000948.7 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   ag14-il100,000547.6 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   ag14-il200,000962.2 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   ag14-il200,000559.4 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ag14-il500,000980.4 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ag14-il500,000576 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   ag14-il1,000,000993.8 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ag14-il1,000,000589.4 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
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