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AG12 (ag12-il)

AG12 - Drela AG12 airfoil


Airfoil ag12-il
Details Dat file Parser  
(ag12-il) AG12
Drela AG12 airfoil
Max thickness 6.2% at 20.8% chord.
Max camber 1.8% at 42.8% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
AG12
     1.000000    0.000471
     0.994142    0.001042
     0.982204    0.002222
     0.968696    0.003522
     0.954910    0.004823
     0.941098    0.006097
     0.927274    0.007345
     0.913441    0.008575
     0.899593    0.009787
     0.885734    0.010985
     0.871861    0.012172
     0.857979    0.013351
     0.844090    0.014522
     0.830201    0.015686
     0.816312    0.016845
     0.802424    0.017996
     0.788539    0.019141
     0.774659    0.020278
     0.760778    0.021407
     0.746901    0.022526
     0.733027    0.023634
     0.719152    0.024731
     0.705280    0.025817
     0.691409    0.026889
     0.677538    0.027948
     0.663670    0.028994
     0.649803    0.030024
     0.635935    0.031038
     0.622068    0.032036
     0.608205    0.033016
     0.594342    0.033978
     0.580478    0.034920
     0.566619    0.035841
     0.552761    0.036741
     0.538905    0.037617
     0.525049    0.038470
     0.511197    0.039296
     0.497347    0.040096
     0.483500    0.040866
     0.469656    0.041607
     0.455816    0.042313
     0.441978    0.042986
     0.428143    0.043622
     0.414316    0.044218
     0.400492    0.044774
     0.386673    0.045285
     0.372861    0.045751
     0.359053    0.046165
     0.345250    0.046528
     0.331461    0.046836
     0.317683    0.047081
     0.303912    0.047262
     0.290156    0.047375
     0.276418    0.047413
     0.262691    0.047371
     0.248985    0.047243
     0.235302    0.047024
     0.221638    0.046704
     0.208004    0.046279
     0.194402    0.045737
     0.180830    0.045066
     0.167304    0.044260
     0.153819    0.043301
     0.140392    0.042180
     0.127049    0.040877
     0.113793    0.039371
     0.100663    0.037640
     0.087677    0.035653
     0.074897    0.033377
     0.062374    0.030770
     0.050223    0.027789
     0.038618    0.024400
     0.027917    0.020611
     0.018756    0.016601
     0.011861    0.012819
     0.007244    0.009642
     0.004260    0.007074
     0.002309    0.004947
     0.001028    0.003119
     0.000261    0.001485
     0.000000   -0.000011
     0.000299   -0.001481
     0.001263   -0.002904
     0.002871   -0.004229
     0.005195   -0.005565
     0.008563   -0.007032
     0.013654   -0.008722
     0.021338   -0.010619
     0.031664   -0.012466
     0.043571   -0.013982
     0.056254   -0.015147
     0.069286   -0.016003
     0.082543   -0.016609
     0.095952   -0.017016
     0.109468   -0.017263
     0.123058   -0.017375
     0.136704   -0.017378
     0.150385   -0.017283
     0.164098   -0.017105
     0.177834   -0.016851
     0.191595   -0.016531
     0.205382   -0.016156
     0.219178   -0.015730
     0.232992   -0.015261
     0.246823   -0.014753
     0.260663   -0.014213
     0.274519   -0.013643
     0.288396   -0.013052
     0.302276   -0.012444
     0.316162   -0.011821
     0.330060   -0.011187
     0.343964   -0.010546
     0.357874   -0.009899
     0.371793   -0.009250
     0.385719   -0.008601
     0.399644   -0.007955
     0.413564   -0.007312
     0.427475   -0.006678
     0.441384   -0.006050
     0.455289   -0.005434
     0.469185   -0.004829
     0.483074   -0.004240
     0.496967   -0.003667
     0.510856   -0.003112
     0.524739   -0.002575
     0.538618   -0.002060
     0.552501   -0.001566
     0.566379   -0.001094
     0.580251   -0.000648
     0.594125   -0.000227
     0.608000    0.000167
     0.621871    0.000536
     0.635737    0.000876
     0.649609    0.001189
     0.663478    0.001474
     0.677342    0.001730
     0.691207    0.001956
     0.705074    0.002153
     0.718938    0.002321
     0.732801    0.002458
     0.746669    0.002565
     0.760534    0.002643
     0.774396    0.002689
     0.788262    0.002707
     0.802128    0.002695
     0.815988    0.002653
     0.829854    0.002581
     0.843721    0.002481
     0.857585    0.002351
     0.871458    0.002194
     0.885322    0.002011
     0.899184    0.001798
     0.913057    0.001557
     0.926935    0.001293
     0.940803    0.001006
     0.954669    0.000690
     0.968513    0.000352
     0.982113   -0.000002
     0.994133   -0.000323
     1.000000   -0.000471
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Polars for AG12 (ag12-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   ag12-il50,000933.2 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ag12-il50,000535.1 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ag12-il100,000947.1 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ag12-il100,000547 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ag12-il200,000961.4 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ag12-il200,000558.7 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ag12-il500,000979.6 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ag12-il500,000574.6 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   ag12-il1,000,000992.6 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ag12-il1,000,000587.1 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
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