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AG11 (ag11-il)

AG11 - Drela AG11 airfoil


Airfoil ag11-il
Details Dat file Parser  
(ag11-il) AG11
Drela AG11 airfoil
Max thickness 5.8% at 26% chord.
Max camber 2.2% at 29.7% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
AG11
     0.999993    0.001223
     0.994925    0.001755
     0.985075    0.002768
     0.973466    0.003923
     0.961158    0.005121
     0.948651    0.006338
     0.936097    0.007566
     0.923528    0.008799
     0.910954    0.010032
     0.898385    0.011266
     0.885822    0.012494
     0.873266    0.013714
     0.860716    0.014928
     0.848169    0.016132
     0.835627    0.017325
     0.823083    0.018508
     0.810541    0.019679
     0.798000    0.020836
     0.785455    0.021982
     0.772910    0.023116
     0.760364    0.024238
     0.747814    0.025348
     0.735261    0.026446
     0.722707    0.027533
     0.710153    0.028609
     0.697598    0.029674
     0.685046    0.030726
     0.672494    0.031764
     0.659944    0.032789
     0.647396    0.033798
     0.634851    0.034791
     0.622307    0.035768
     0.609766    0.036729
     0.597227    0.037672
     0.584690    0.038592
     0.572156    0.039497
     0.559627    0.040376
     0.547098    0.041233
     0.534573    0.042066
     0.522050    0.042874
     0.509530    0.043655
     0.497013    0.044410
     0.484499    0.045138
     0.471986    0.045833
     0.459477    0.046499
     0.446970    0.047132
     0.434464    0.047732
     0.421962    0.048300
     0.409462    0.048832
     0.396966    0.049327
     0.384475    0.049783
     0.371988    0.050202
     0.359508    0.050580
     0.347036    0.050913
     0.334570    0.051203
     0.322115    0.051446
     0.309670    0.051636
     0.297238    0.051776
     0.284818    0.051861
     0.272415    0.051884
     0.260032    0.051845
     0.247668    0.051740
     0.235328    0.051562
     0.223016    0.051308
     0.210734    0.050971
     0.198489    0.050544
     0.186288    0.050022
     0.174136    0.049395
     0.162040    0.048658
     0.150014    0.047797
     0.138068    0.046804
     0.126220    0.045661
     0.114485    0.044362
     0.102894    0.042885
     0.091474    0.041217
     0.080272    0.039336
     0.069343    0.037223
     0.058771    0.034868
     0.048687    0.032263
     0.039320    0.029440
     0.031003    0.026481
     0.024078    0.023543
     0.018682    0.020809
     0.014619    0.018390
     0.011588    0.016304
     0.009315    0.014517
     0.007580    0.012982
     0.006126    0.011544
     0.004978    0.010283
     0.004054    0.009164
     0.003275    0.008122
     0.002609    0.007135
     0.001990    0.006109
     0.001459    0.005102
     0.000846    0.003721
     0.000277    0.001914
     0.000030    0.000612
     0.000057   -0.000862
     0.000494   -0.002341
     0.001555   -0.003498
     0.003329   -0.004392
     0.005621   -0.005083
     0.011180   -0.006096
     0.018541   -0.006861
     0.027907   -0.007425
     0.038894   -0.007784
     0.050498   -0.007961
     0.062582   -0.008015
     0.075052   -0.007986
     0.087786   -0.007903
     0.100701   -0.007785
     0.113749   -0.007644
     0.126891   -0.007488
     0.140109   -0.007328
     0.153387   -0.007171
     0.165787   -0.007032
     0.178228   -0.006904
     0.190707   -0.006779
     0.203222   -0.006668
     0.215768   -0.006584
     0.228345   -0.006499
     0.240940   -0.006413
     0.253559   -0.006324
     0.266192   -0.006235
     0.278838   -0.006148
     0.291489   -0.006058
     0.304142   -0.005970
     0.316794   -0.005882
     0.329439   -0.005792
     0.342078   -0.005705
     0.354713   -0.005616
     0.367343   -0.005527
     0.379970   -0.005439
     0.392591   -0.005351
     0.405210   -0.005263
     0.417825   -0.005174
     0.430435   -0.005086
     0.443043   -0.004998
     0.455648   -0.004910
     0.468257   -0.004822
     0.480868   -0.004732
     0.493486   -0.004645
     0.506103   -0.004556
     0.518723   -0.004467
     0.531339   -0.004379
     0.543953   -0.004292
     0.556568   -0.004202
     0.569182   -0.004114
     0.581795   -0.004026
     0.594407   -0.003938
     0.607018   -0.003850
     0.619632   -0.003762
     0.632244   -0.003674
     0.644857   -0.003584
     0.657466   -0.003497
     0.670080   -0.003409
     0.682691   -0.003320
     0.695305   -0.003231
     0.707918   -0.003143
     0.720535   -0.003056
     0.733151   -0.002966
     0.745769   -0.002878
     0.758388   -0.002790
     0.771009   -0.002702
     0.783632   -0.002614
     0.796259   -0.002525
     0.808887   -0.002436
     0.821518   -0.002350
     0.834154   -0.002259
     0.846797   -0.002171
     0.859444   -0.002082
     0.872099   -0.001995
     0.884756   -0.001905
     0.897410   -0.001816
     0.910058   -0.001728
     0.922707   -0.001640
     0.935355   -0.001552
     0.947998   -0.001463
     0.960606   -0.001374
     0.973049   -0.001288
     0.984857   -0.001204
     0.994859   -0.001135
     1.000007   -0.001098
Dat file parser warnings
  • Line 184 - X value too large but included: 1.000007 -0.001098
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Selig format dat file

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Polars for AG11 (ag11-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   ag11-il50,000933 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ag11-il50,000534.6 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ag11-il100,000946.7 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   ag11-il100,000546.1 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   ag11-il200,000959.9 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   ag11-il200,000558.1 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   ag11-il500,000977.8 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   ag11-il500,000575.7 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   ag11-il1,000,000991.8 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   ag11-il1,000,000591 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
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