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AG16 (ag16-il)

AG16 - Drela AG16 airfoil


Airfoil ag16-il
Details Dat file Parser  
(ag16-il) AG16
Drela AG16 airfoil
Max thickness 7.1% at 23.4% chord.
Max camber 1.9% at 46.9% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
AG16
     0.999982    0.000259
     0.994055    0.000895
     0.982059    0.002185
     0.968510    0.003609
     0.954662    0.005047
     0.940774    0.006484
     0.926885    0.007912
     0.912993    0.009331
     0.899100    0.010743
     0.885210    0.012146
     0.871319    0.013539
     0.857433    0.014921
     0.843545    0.016291
     0.829661    0.017647
     0.815777    0.018989
     0.801890    0.020318
     0.788007    0.021631
     0.774122    0.022928
     0.760234    0.024210
     0.746349    0.025476
     0.732460    0.026726
     0.718568    0.027960
     0.704680    0.029179
     0.690792    0.030379
     0.676901    0.031561
     0.663014    0.032725
     0.649130    0.033868
     0.635243    0.034990
     0.621358    0.036090
     0.607477    0.037166
     0.593595    0.038217
     0.579713    0.039243
     0.565836    0.040241
     0.551961    0.041210
     0.538084    0.042148
     0.524210    0.043055
     0.510343    0.043927
     0.496475    0.044762
     0.482606    0.045562
     0.468743    0.046323
     0.454885    0.047041
     0.441027    0.047716
     0.427174    0.048347
     0.413328    0.048928
     0.399483    0.049459
     0.385642    0.049937
     0.371812    0.050359
     0.357986    0.050720
     0.344163    0.051021
     0.330353    0.051256
     0.316555    0.051420
     0.302760    0.051509
     0.288982    0.051522
     0.275220    0.051450
     0.261465    0.051289
     0.247732    0.051036
     0.234021    0.050681
     0.220327    0.050219
     0.206665    0.049643
     0.193035    0.048942
     0.179439    0.048108
     0.165899    0.047128
     0.152408    0.045986
     0.138987    0.044671
     0.125653    0.043158
     0.112413    0.041431
     0.099311    0.039463
     0.086363    0.037222
     0.073635    0.034678
     0.061172    0.031787
     0.049093    0.028512
     0.037574    0.024830
     0.026987    0.020770
     0.018028    0.016568
     0.011373    0.012701
     0.006948    0.009495
     0.004080    0.006919
     0.002203    0.004781
     0.000968    0.002947
     0.000230    0.001312
     0.000000   -0.000195
     0.000341   -0.001673
     0.001328   -0.003130
     0.002935   -0.004552
     0.005261   -0.006046
     0.008653   -0.007730
     0.013784   -0.009725
     0.021492   -0.012025
     0.031716   -0.014331
     0.043529   -0.016291
     0.056132   -0.017887
     0.069116   -0.019147
     0.082329   -0.020122
     0.095697   -0.020863
     0.109171   -0.021400
     0.122724   -0.021765
     0.136334   -0.021977
     0.149994   -0.022057
     0.163688   -0.022019
     0.177415   -0.021877
     0.191166   -0.021644
     0.204936   -0.021333
     0.218725   -0.020952
     0.232530   -0.020509
     0.246346   -0.020012
     0.260179   -0.019469
     0.274022   -0.018884
     0.287877   -0.018267
     0.301747   -0.017627
     0.315629   -0.016960
     0.329522   -0.016271
     0.343431   -0.015563
     0.357351   -0.014841
     0.371284   -0.014106
     0.385229   -0.013364
     0.399185   -0.012615
     0.413144   -0.011865
     0.427092   -0.011116
     0.441028   -0.010373
     0.454954   -0.009635
     0.468873   -0.008906
     0.482781   -0.008188
     0.496682   -0.007484
     0.510577   -0.006794
     0.524471   -0.006121
     0.538359   -0.005465
     0.552243   -0.004831
     0.566124   -0.004218
     0.580004   -0.003628
     0.593877   -0.003061
     0.607748   -0.002521
     0.621614   -0.002007
     0.635476   -0.001521
     0.649333   -0.001064
     0.663189   -0.000637
     0.677044   -0.000238
     0.690898    0.000128
     0.704753    0.000461
     0.718610    0.000764
     0.732471    0.001032
     0.746331    0.001265
     0.760195    0.001469
     0.774062    0.001633
     0.787929    0.001765
     0.801802    0.001863
     0.815681    0.001921
     0.829560    0.001944
     0.843441    0.001932
     0.857326    0.001883
     0.871211    0.001799
     0.885098    0.001680
     0.898988    0.001521
     0.912876    0.001324
     0.926767    0.001097
     0.940657    0.000839
     0.954550    0.000538
     0.968415    0.000208
     0.982033   -0.000149
     0.994056   -0.000494
     1.000001   -0.000670
Dat file parser warnings
  • Line 161 - X value too large but included: 1.000001 -0.000670
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Polars for AG16 (ag16-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   ag16-il50,000933.5 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   ag16-il50,000536 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   ag16-il100,000948.6 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   ag16-il100,000548.4 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ag16-il200,000963.6 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ag16-il200,000560.3 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ag16-il500,000982.4 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   ag16-il500,000576.3 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   ag16-il1,000,000995.3 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   ag16-il1,000,000588.4 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
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