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AG38 (ag38-il)

AG38 - Drela AG38 airfoil


Airfoil ag38-il
Details Dat file Parser  
(ag38-il) AG38
Drela AG38 airfoil
Max thickness 7% at 27.7% chord.
Max camber 2% at 36.7% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
AG38
     0.999999    0.004704
     0.993621    0.005696
     0.983682    0.007241
     0.972066    0.009047
     0.959633    0.010981
     0.946835    0.012971
     0.933981    0.014969
     0.921234    0.016952
     0.908447    0.018940
     0.895764    0.020914
     0.882852    0.022914
     0.870677    0.024564
     0.857810    0.026064
     0.844779    0.027481
     0.831613    0.028913
     0.818263    0.030364
     0.804818    0.031827
     0.791388    0.033286
     0.777951    0.034747
     0.764549    0.036205
     0.751106    0.037667
     0.737702    0.039124
     0.724342    0.040577
     0.711051    0.042022
     0.697928    0.043448
     0.685186    0.044836
     0.672293    0.046199
     0.658783    0.047537
     0.647516    0.048556
     0.635011    0.049622
     0.622485    0.050624
     0.609531    0.051627
     0.596533    0.052634
     0.583312    0.053658
     0.569976    0.054692
     0.556633    0.055727
     0.543315    0.056758
     0.530000    0.057791
     0.516728    0.058820
     0.503472    0.059846
     0.490290    0.060869
     0.477236    0.061880
     0.464539    0.062866
     0.452148    0.063819
     0.439870    0.064696
     0.427640    0.065505
     0.415386    0.066252
     0.403250    0.066927
     0.391172    0.067542
     0.379063    0.068100
     0.366729    0.068612
     0.354113    0.069073
     0.341333    0.069479
     0.328488    0.069821
     0.315654    0.070095
     0.302897    0.070294
     0.290182    0.070419
     0.277486    0.070467
     0.264739    0.070440
     0.251950    0.070331
     0.239044    0.070136
     0.226021    0.069844
     0.212912    0.069446
     0.199800    0.068938
     0.186742    0.068312
     0.173780    0.067562
     0.160907    0.066679
     0.148128    0.065652
     0.135369    0.064462
     0.122667    0.063091
     0.110044    0.061522
     0.097563    0.059738
     0.086115    0.057868
     0.075071    0.055815
     0.064507    0.053584
     0.054572    0.051199
     0.045308    0.048667
     0.036786    0.046008
     0.029161    0.043281
     0.022616    0.040585
     0.017243    0.038018
     0.012940    0.035620
     0.009579    0.033433
     0.007013    0.031471
     0.005102    0.029742
     0.003685    0.028228
     0.002589    0.026840
     0.001700    0.025486
     0.000978    0.024106
     0.000451    0.022746
     0.000094    0.021225
     0.000009    0.019745
     0.000172    0.018622
     0.000581    0.017457
     0.001293    0.016280
     0.002383    0.015135
     0.003836    0.014081
     0.005649    0.013115
     0.007886    0.012203
     0.010612    0.011326
     0.013931    0.010463
     0.018027    0.009582
     0.023174    0.008665
     0.029676    0.007708
     0.037756    0.006738
     0.047349    0.005792
     0.058120    0.004930
     0.069666    0.004170
     0.081678    0.003507
     0.093975    0.002937
     0.106461    0.002451
     0.119072    0.002040
     0.131774    0.001694
     0.144550    0.001399
     0.157380    0.001147
     0.170260    0.000929
     0.183177    0.000744
     0.196137    0.000585
     0.209128    0.000450
     0.222152    0.000335
     0.235196    0.000245
     0.248262    0.000172
     0.261351    0.000117
     0.274460    0.000077
     0.287589    0.000040
     0.300735    0.000018
     0.313898    0.000004
     0.327086   -0.000005
     0.340287   -0.000003
     0.353486   -0.000003
     0.366689   -0.000003
     0.379895   -0.000001
     0.393109   -0.000003
     0.406322   -0.000002
     0.419532    0.000001
     0.432737   -0.000003
     0.445943    0.000001
     0.459157    0.000002
     0.472370   -0.000001
     0.485577    0.000002
     0.498782    0.000001
     0.511992    0.000000
     0.525205    0.000001
     0.538418   -0.000001
     0.551625   -0.000001
     0.564826    0.000001
     0.578028   -0.000001
     0.591236   -0.000002
     0.604443    0.000000
     0.617649    0.000000
     0.630860   -0.000001
     0.644076    0.000000
     0.657286    0.000000
     0.670495    0.000002
     0.683700    0.000000
     0.696909    0.000001
     0.710122   -0.000001
     0.723334    0.000000
     0.736542   -0.000002
     0.749746   -0.000002
     0.762958   -0.000001
     0.776172    0.000000
     0.789383    0.000000
     0.802589    0.000001
     0.815788    0.000001
     0.828992    0.000001
     0.842199    0.000002
     0.855403   -0.000002
     0.868602   -0.000002
     0.881798   -0.000002
     0.895001   -0.000002
     0.908208   -0.000001
     0.921420    0.000000
     0.934616    0.000001
     0.947766    0.000002
     0.960776    0.000000
     0.973384    0.000000
     0.984990    0.000000
     0.994806    0.000000
     1.000000    0.000001
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Lednicer format dat file
Selig format dat file

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Polars for AG38 (ag38-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   ag38-il50,000934.2 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   ag38-il50,000536 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   ag38-il100,000949.1 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   ag38-il100,000548.4 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ag38-il200,000964 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   ag38-il200,000559.3 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
   ag38-il500,000981.3 at α=2.75°Mach=0 Ncrit=9Xfoil predictionDetails
   ag38-il500,000573.5 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ag38-il1,000,000992 at α=3°Mach=0 Ncrit=9Xfoil predictionDetails
   ag38-il1,000,000585.8 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
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