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AG10 (ag10-il)

AG10 - Drela AG10 airfoil


Airfoil ag10-il
Details Dat file Parser  
(ag10-il) AG10
Drela AG10 airfoil
Max thickness 4.7% at 16% chord.
Max camber 1.7% at 32.1% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
AG10
     0.999974    0.002176
     0.994846    0.002555
     0.984945    0.003283
     0.973279    0.004131
     0.960914    0.005022
     0.948350    0.005919
     0.935739    0.006810
     0.923111    0.007691
     0.910478    0.008564
     0.897850    0.009428
     0.885229    0.010282
     0.872617    0.011125
     0.860009    0.011960
     0.847406    0.012783
     0.834807    0.013598
     0.822210    0.014402
     0.809614    0.015199
     0.797021    0.015985
     0.784426    0.016764
     0.771830    0.017536
     0.759236    0.018297
     0.746639    0.019053
     0.734038    0.019797
     0.721440    0.020531
     0.708839    0.021256
     0.696240    0.021971
     0.683641    0.022674
     0.671048    0.023367
     0.658455    0.024048
     0.645865    0.024721
     0.633280    0.025378
     0.620699    0.026029
     0.608123    0.026670
     0.595552    0.027299
     0.582988    0.027919
     0.570436    0.028523
     0.557889    0.029115
     0.545349    0.029697
     0.532818    0.030265
     0.520296    0.030820
     0.507781    0.031365
     0.495276    0.031894
     0.482780    0.032414
     0.470292    0.032920
     0.457812    0.033415
     0.445340    0.033898
     0.432874    0.034369
     0.420416    0.034829
     0.407964    0.035275
     0.395519    0.035708
     0.383083    0.036126
     0.370651    0.036530
     0.358228    0.036916
     0.345814    0.037284
     0.333403    0.037629
     0.320995    0.037950
     0.308592    0.038244
     0.296191    0.038506
     0.283793    0.038733
     0.271398    0.038920
     0.259004    0.039061
     0.246612    0.039153
     0.234221    0.039188
     0.221833    0.039162
     0.209446    0.039064
     0.197067    0.038889
     0.184693    0.038628
     0.172330    0.038271
     0.159986    0.037809
     0.147685    0.037231
     0.135454    0.036526
     0.123360    0.035684
     0.111394    0.034690
     0.099596    0.033528
     0.088011    0.032181
     0.076685    0.030635
     0.065663    0.028864
     0.055015    0.026849
     0.044865    0.024579
     0.035426    0.022076
     0.027030    0.019427
     0.019970    0.016771
     0.014377    0.014268
     0.010159    0.012029
     0.007009    0.010051
     0.004650    0.008292
     0.002879    0.006696
     0.001578    0.005207
     0.000698    0.003785
     0.000198    0.002434
     0.000000    0.001190
     0.000000    0.000000
     0.000258   -0.001992
     0.000832   -0.003348
     0.001858   -0.004711
     0.003426   -0.005982
     0.005568   -0.007173
     0.008409   -0.008303
     0.012185   -0.009379
     0.017243   -0.010404
     0.023929   -0.011326
     0.032338   -0.012056
     0.042155   -0.012532
     0.052898   -0.012742
     0.064198   -0.012720
     0.075846   -0.012533
     0.087736   -0.012223
     0.099803   -0.011837
     0.111997   -0.011398
     0.124285   -0.010925
     0.136634   -0.010429
     0.149040   -0.009918
     0.161493   -0.009400
     0.173985   -0.008878
     0.186517   -0.008359
     0.199087   -0.007845
     0.211686   -0.007340
     0.224315   -0.006846
     0.236968   -0.006364
     0.249641   -0.005898
     0.262329   -0.005451
     0.275030   -0.005022
     0.287738   -0.004615
     0.300450   -0.004231
     0.313158   -0.003870
     0.325864   -0.003534
     0.338565   -0.003224
     0.351261   -0.002939
     0.363955   -0.002680
     0.376646   -0.002447
     0.389333   -0.002239
     0.402018   -0.002057
     0.414702   -0.001899
     0.427381   -0.001766
     0.440057   -0.001656
     0.452730   -0.001566
     0.465409   -0.001496
     0.478092   -0.001443
     0.490780   -0.001407
     0.503470   -0.001381
     0.516157   -0.001369
     0.528844   -0.001364
     0.541527   -0.001368
     0.554213   -0.001376
     0.566894   -0.001386
     0.579575   -0.001398
     0.592254   -0.001410
     0.604934   -0.001424
     0.617614   -0.001434
     0.630291   -0.001437
     0.642967   -0.001443
     0.655644   -0.001442
     0.668323   -0.001439
     0.681003   -0.001437
     0.693683   -0.001440
     0.706365   -0.001442
     0.719048   -0.001444
     0.731731   -0.001446
     0.744416   -0.001443
     0.757102   -0.001445
     0.769790   -0.001444
     0.782480   -0.001445
     0.795173   -0.001446
     0.807870   -0.001446
     0.820569   -0.001446
     0.833273   -0.001446
     0.845984   -0.001448
     0.858698   -0.001448
     0.871422   -0.001451
     0.884148   -0.001448
     0.896868   -0.001446
     0.909585   -0.001443
     0.922302   -0.001445
     0.935019   -0.001446
     0.947730   -0.001446
     0.960405   -0.001439
     0.972917   -0.001437
     0.984788   -0.001441
     0.994843   -0.001441
     1.000019   -0.001441
Dat file parser warnings
  • Line 181 - X value too large but included: 1.000019 -0.001441
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Lednicer format dat file
Selig format dat file

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Polars for AG10 (ag10-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   ag10-il50,000931.2 at α=3°Mach=0 Ncrit=9Xfoil predictionDetails
   ag10-il50,000531 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ag10-il100,000941.2 at α=2.5°Mach=0 Ncrit=9Xfoil predictionDetails
   ag10-il100,000541.7 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   ag10-il200,000952.6 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   ag10-il200,000552.7 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   ag10-il500,000969.8 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   ag10-il500,000567.5 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   ag10-il1,000,000981.9 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   ag10-il1,000,000579.6 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
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