AG10 (ag10-il)
AG10 - Drela AG10 airfoil
| Details | Dat file | Parser | |
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(ag10-il) AG10 Drela AG10 airfoil Max thickness 4.7% at 16% chord. Max camber 1.7% at 32.1% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
AG10
0.999974 0.002176
0.994846 0.002555
0.984945 0.003283
0.973279 0.004131
0.960914 0.005022
0.948350 0.005919
0.935739 0.006810
0.923111 0.007691
0.910478 0.008564
0.897850 0.009428
0.885229 0.010282
0.872617 0.011125
0.860009 0.011960
0.847406 0.012783
0.834807 0.013598
0.822210 0.014402
0.809614 0.015199
0.797021 0.015985
0.784426 0.016764
0.771830 0.017536
0.759236 0.018297
0.746639 0.019053
0.734038 0.019797
0.721440 0.020531
0.708839 0.021256
0.696240 0.021971
0.683641 0.022674
0.671048 0.023367
0.658455 0.024048
0.645865 0.024721
0.633280 0.025378
0.620699 0.026029
0.608123 0.026670
0.595552 0.027299
0.582988 0.027919
0.570436 0.028523
0.557889 0.029115
0.545349 0.029697
0.532818 0.030265
0.520296 0.030820
0.507781 0.031365
0.495276 0.031894
0.482780 0.032414
0.470292 0.032920
0.457812 0.033415
0.445340 0.033898
0.432874 0.034369
0.420416 0.034829
0.407964 0.035275
0.395519 0.035708
0.383083 0.036126
0.370651 0.036530
0.358228 0.036916
0.345814 0.037284
0.333403 0.037629
0.320995 0.037950
0.308592 0.038244
0.296191 0.038506
0.283793 0.038733
0.271398 0.038920
0.259004 0.039061
0.246612 0.039153
0.234221 0.039188
0.221833 0.039162
0.209446 0.039064
0.197067 0.038889
0.184693 0.038628
0.172330 0.038271
0.159986 0.037809
0.147685 0.037231
0.135454 0.036526
0.123360 0.035684
0.111394 0.034690
0.099596 0.033528
0.088011 0.032181
0.076685 0.030635
0.065663 0.028864
0.055015 0.026849
0.044865 0.024579
0.035426 0.022076
0.027030 0.019427
0.019970 0.016771
0.014377 0.014268
0.010159 0.012029
0.007009 0.010051
0.004650 0.008292
0.002879 0.006696
0.001578 0.005207
0.000698 0.003785
0.000198 0.002434
0.000000 0.001190
0.000000 0.000000
0.000258 -0.001992
0.000832 -0.003348
0.001858 -0.004711
0.003426 -0.005982
0.005568 -0.007173
0.008409 -0.008303
0.012185 -0.009379
0.017243 -0.010404
0.023929 -0.011326
0.032338 -0.012056
0.042155 -0.012532
0.052898 -0.012742
0.064198 -0.012720
0.075846 -0.012533
0.087736 -0.012223
0.099803 -0.011837
0.111997 -0.011398
0.124285 -0.010925
0.136634 -0.010429
0.149040 -0.009918
0.161493 -0.009400
0.173985 -0.008878
0.186517 -0.008359
0.199087 -0.007845
0.211686 -0.007340
0.224315 -0.006846
0.236968 -0.006364
0.249641 -0.005898
0.262329 -0.005451
0.275030 -0.005022
0.287738 -0.004615
0.300450 -0.004231
0.313158 -0.003870
0.325864 -0.003534
0.338565 -0.003224
0.351261 -0.002939
0.363955 -0.002680
0.376646 -0.002447
0.389333 -0.002239
0.402018 -0.002057
0.414702 -0.001899
0.427381 -0.001766
0.440057 -0.001656
0.452730 -0.001566
0.465409 -0.001496
0.478092 -0.001443
0.490780 -0.001407
0.503470 -0.001381
0.516157 -0.001369
0.528844 -0.001364
0.541527 -0.001368
0.554213 -0.001376
0.566894 -0.001386
0.579575 -0.001398
0.592254 -0.001410
0.604934 -0.001424
0.617614 -0.001434
0.630291 -0.001437
0.642967 -0.001443
0.655644 -0.001442
0.668323 -0.001439
0.681003 -0.001437
0.693683 -0.001440
0.706365 -0.001442
0.719048 -0.001444
0.731731 -0.001446
0.744416 -0.001443
0.757102 -0.001445
0.769790 -0.001444
0.782480 -0.001445
0.795173 -0.001446
0.807870 -0.001446
0.820569 -0.001446
0.833273 -0.001446
0.845984 -0.001448
0.858698 -0.001448
0.871422 -0.001451
0.884148 -0.001448
0.896868 -0.001446
0.909585 -0.001443
0.922302 -0.001445
0.935019 -0.001446
0.947730 -0.001446
0.960405 -0.001439
0.972917 -0.001437
0.984788 -0.001441
0.994843 -0.001441
1.000019 -0.001441
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Dat file parser warnings
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Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
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Polars for AG10 (ag10-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ag10-il | 50,000 | 9 | 31.2 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag10-il | 50,000 | 5 | 31 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag10-il | 100,000 | 9 | 41.2 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag10-il | 100,000 | 5 | 41.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag10-il | 200,000 | 9 | 52.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag10-il | 200,000 | 5 | 52.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag10-il | 500,000 | 9 | 69.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag10-il | 500,000 | 5 | 67.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag10-il | 1,000,000 | 9 | 81.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag10-il | 1,000,000 | 5 | 79.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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