AG08 (ag08-il)
AG08 - Drela AG08 airfoil
| Details | Dat file | Parser | |
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(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
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Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
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Polars for AG08 (ag08-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ag08-il | 50,000 | 9 | 32.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag08-il | 50,000 | 5 | 33.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag08-il | 100,000 | 9 | 45.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag08-il | 100,000 | 5 | 45.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag08-il | 200,000 | 9 | 58.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag08-il | 200,000 | 5 | 56.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag08-il | 500,000 | 9 | 76.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag08-il | 500,000 | 5 | 72 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag08-il | 1,000,000 | 9 | 89 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag08-il | 1,000,000 | 5 | 83.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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