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AG08 (ag08-il)

AG08 - Drela AG08 airfoil


Airfoil ag08-il
Details Dat file Parser  
(ag08-il) AG08
Drela AG08 airfoil
Max thickness 5.8% at 21% chord.
Max camber 1.7% at 40.4% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
AG08
     0.999995    0.000806
     0.995523    0.001246
     0.986211    0.002157
     0.974697    0.003274
     0.962305    0.004464
     0.949501    0.005676
     0.936651    0.006880
     0.923780    0.008068
     0.910885    0.009241
     0.897997    0.010399
     0.885107    0.011541
     0.872208    0.012668
     0.859309    0.013781
     0.846401    0.014881
     0.833498    0.015965
     0.820589    0.017036
     0.807673    0.018096
     0.794763    0.019141
     0.781843    0.020174
     0.768925    0.021194
     0.756016    0.022200
     0.743098    0.023193
     0.730173    0.024173
     0.717267    0.025138
     0.704348    0.026088
     0.691426    0.027027
     0.678518    0.027948
     0.665598    0.028855
     0.652686    0.029746
     0.639778    0.030622
     0.626867    0.031480
     0.613959    0.032320
     0.601057    0.033143
     0.588151    0.033947
     0.575254    0.034731
     0.562357    0.035493
     0.549457    0.036236
     0.536569    0.036958
     0.523678    0.037655
     0.510793    0.038329
     0.497907    0.038978
     0.485015    0.039606
     0.472140    0.040207
     0.459256    0.040782
     0.446379    0.041331
     0.433512    0.041852
     0.420638    0.042344
     0.407777    0.042808
     0.394921    0.043240
     0.382067    0.043640
     0.369226    0.044006
     0.356394    0.044335
     0.343571    0.044626
     0.330763    0.044878
     0.317974    0.045085
     0.305201    0.045244
     0.292443    0.045352
     0.279711    0.045408
     0.267002    0.045403
     0.254318    0.045335
     0.241668    0.045199
     0.229055    0.044988
     0.216471    0.044695
     0.203932    0.044318
     0.191446    0.043846
     0.179007    0.043271
     0.166640    0.042587
     0.154357    0.041780
     0.142151    0.040838
     0.130047    0.039755
     0.118076    0.038511
     0.106223    0.037091
     0.094545    0.035487
     0.083078    0.033677
     0.071857    0.031647
     0.060981    0.029384
     0.050548    0.026881
     0.040753    0.024157
     0.031885    0.021285
     0.024285    0.018407
     0.018183    0.015708
     0.013512    0.013310
     0.009983    0.011224
     0.007293    0.009399
     0.005208    0.007775
     0.003567    0.006301
     0.002279    0.004935
     0.001295    0.003653
     0.000593    0.002433
     0.000171    0.001292
     0.000006    0.000246
     0.000067   -0.000766
     0.000403   -0.001805
     0.001077   -0.002877
     0.002060   -0.003930
     0.003341   -0.004949
     0.004937   -0.005945
     0.006901   -0.006940
     0.009341   -0.007956
     0.012439   -0.009018
     0.016472   -0.010141
     0.021797   -0.011319
     0.028804   -0.012513
     0.037560   -0.013612
     0.047692   -0.014504
     0.058754   -0.015165
     0.070390   -0.015617
     0.082387   -0.015896
     0.094618   -0.016032
     0.107019   -0.016053
     0.119570   -0.015973
     0.132227   -0.015808
     0.144960   -0.015577
     0.157770   -0.015294
     0.170648   -0.014968
     0.183570   -0.014608
     0.196531   -0.014218
     0.209521   -0.013805
     0.222525   -0.013372
     0.235525   -0.012920
     0.248492   -0.012455
     0.261450   -0.011981
     0.274408   -0.011498
     0.287353   -0.011014
     0.300284   -0.010529
     0.313224   -0.010048
     0.326153   -0.009571
     0.339075   -0.009101
     0.352006   -0.008640
     0.364929   -0.008186
     0.377848   -0.007746
     0.390775   -0.007317
     0.403702   -0.006901
     0.416621   -0.006500
     0.429544   -0.006113
     0.442473   -0.005744
     0.455394   -0.005390
     0.468324   -0.005055
     0.481272   -0.004736
     0.494202   -0.004434
     0.507143   -0.004151
     0.520098   -0.003887
     0.533047   -0.003637
     0.546003   -0.003407
     0.558983   -0.003192
     0.571964   -0.002991
     0.584943   -0.002808
     0.597933   -0.002638
     0.610921   -0.002488
     0.623904   -0.002349
     0.636890   -0.002226
     0.649890   -0.002115
     0.662896   -0.002020
     0.675895   -0.001932
     0.688898   -0.001856
     0.701904   -0.001788
     0.714908   -0.001728
     0.727913   -0.001672
     0.740922   -0.001623
     0.753923   -0.001577
     0.766931   -0.001532
     0.779943   -0.001492
     0.792949   -0.001448
     0.805957   -0.001408
     0.818973   -0.001371
     0.831992   -0.001333
     0.845007   -0.001292
     0.858020   -0.001257
     0.871035   -0.001219
     0.884049   -0.001179
     0.897061   -0.001138
     0.910076   -0.001094
     0.923097   -0.001053
     0.936110   -0.001011
     0.949098   -0.000967
     0.962034   -0.000929
     0.974545   -0.000883
     0.986144   -0.000842
     0.995510   -0.000810
     1.000006   -0.000793
Dat file parser warnings
  • Line 181 - X value too large but included: 1.000006 -0.000793
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Lednicer format dat file
Selig format dat file

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Polars for AG08 (ag08-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   ag08-il50,000932.8 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   ag08-il50,000533.8 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ag08-il100,000945.6 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   ag08-il100,000545.1 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ag08-il200,000958.3 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   ag08-il200,000556.6 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   ag08-il500,000976.2 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   ag08-il500,000572 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ag08-il1,000,000989 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   ag08-il1,000,000583.2 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
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