AG11 (ag11-il)
AG11 - Drela AG11 airfoil
| Details | Dat file | Parser | |
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(ag11-il) AG11 Drela AG11 airfoil Max thickness 5.8% at 26% chord. Max camber 2.2% at 29.7% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
AG11
0.999993 0.001223
0.994925 0.001755
0.985075 0.002768
0.973466 0.003923
0.961158 0.005121
0.948651 0.006338
0.936097 0.007566
0.923528 0.008799
0.910954 0.010032
0.898385 0.011266
0.885822 0.012494
0.873266 0.013714
0.860716 0.014928
0.848169 0.016132
0.835627 0.017325
0.823083 0.018508
0.810541 0.019679
0.798000 0.020836
0.785455 0.021982
0.772910 0.023116
0.760364 0.024238
0.747814 0.025348
0.735261 0.026446
0.722707 0.027533
0.710153 0.028609
0.697598 0.029674
0.685046 0.030726
0.672494 0.031764
0.659944 0.032789
0.647396 0.033798
0.634851 0.034791
0.622307 0.035768
0.609766 0.036729
0.597227 0.037672
0.584690 0.038592
0.572156 0.039497
0.559627 0.040376
0.547098 0.041233
0.534573 0.042066
0.522050 0.042874
0.509530 0.043655
0.497013 0.044410
0.484499 0.045138
0.471986 0.045833
0.459477 0.046499
0.446970 0.047132
0.434464 0.047732
0.421962 0.048300
0.409462 0.048832
0.396966 0.049327
0.384475 0.049783
0.371988 0.050202
0.359508 0.050580
0.347036 0.050913
0.334570 0.051203
0.322115 0.051446
0.309670 0.051636
0.297238 0.051776
0.284818 0.051861
0.272415 0.051884
0.260032 0.051845
0.247668 0.051740
0.235328 0.051562
0.223016 0.051308
0.210734 0.050971
0.198489 0.050544
0.186288 0.050022
0.174136 0.049395
0.162040 0.048658
0.150014 0.047797
0.138068 0.046804
0.126220 0.045661
0.114485 0.044362
0.102894 0.042885
0.091474 0.041217
0.080272 0.039336
0.069343 0.037223
0.058771 0.034868
0.048687 0.032263
0.039320 0.029440
0.031003 0.026481
0.024078 0.023543
0.018682 0.020809
0.014619 0.018390
0.011588 0.016304
0.009315 0.014517
0.007580 0.012982
0.006126 0.011544
0.004978 0.010283
0.004054 0.009164
0.003275 0.008122
0.002609 0.007135
0.001990 0.006109
0.001459 0.005102
0.000846 0.003721
0.000277 0.001914
0.000030 0.000612
0.000057 -0.000862
0.000494 -0.002341
0.001555 -0.003498
0.003329 -0.004392
0.005621 -0.005083
0.011180 -0.006096
0.018541 -0.006861
0.027907 -0.007425
0.038894 -0.007784
0.050498 -0.007961
0.062582 -0.008015
0.075052 -0.007986
0.087786 -0.007903
0.100701 -0.007785
0.113749 -0.007644
0.126891 -0.007488
0.140109 -0.007328
0.153387 -0.007171
0.165787 -0.007032
0.178228 -0.006904
0.190707 -0.006779
0.203222 -0.006668
0.215768 -0.006584
0.228345 -0.006499
0.240940 -0.006413
0.253559 -0.006324
0.266192 -0.006235
0.278838 -0.006148
0.291489 -0.006058
0.304142 -0.005970
0.316794 -0.005882
0.329439 -0.005792
0.342078 -0.005705
0.354713 -0.005616
0.367343 -0.005527
0.379970 -0.005439
0.392591 -0.005351
0.405210 -0.005263
0.417825 -0.005174
0.430435 -0.005086
0.443043 -0.004998
0.455648 -0.004910
0.468257 -0.004822
0.480868 -0.004732
0.493486 -0.004645
0.506103 -0.004556
0.518723 -0.004467
0.531339 -0.004379
0.543953 -0.004292
0.556568 -0.004202
0.569182 -0.004114
0.581795 -0.004026
0.594407 -0.003938
0.607018 -0.003850
0.619632 -0.003762
0.632244 -0.003674
0.644857 -0.003584
0.657466 -0.003497
0.670080 -0.003409
0.682691 -0.003320
0.695305 -0.003231
0.707918 -0.003143
0.720535 -0.003056
0.733151 -0.002966
0.745769 -0.002878
0.758388 -0.002790
0.771009 -0.002702
0.783632 -0.002614
0.796259 -0.002525
0.808887 -0.002436
0.821518 -0.002350
0.834154 -0.002259
0.846797 -0.002171
0.859444 -0.002082
0.872099 -0.001995
0.884756 -0.001905
0.897410 -0.001816
0.910058 -0.001728
0.922707 -0.001640
0.935355 -0.001552
0.947998 -0.001463
0.960606 -0.001374
0.973049 -0.001288
0.984857 -0.001204
0.994859 -0.001135
1.000007 -0.001098
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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 AG11 (ag11-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ag11-il | 50,000 | 9 | 33 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag11-il | 50,000 | 5 | 34.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag11-il | 100,000 | 9 | 46.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag11-il | 100,000 | 5 | 46.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag11-il | 200,000 | 9 | 59.9 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag11-il | 200,000 | 5 | 58.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag11-il | 500,000 | 9 | 77.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag11-il | 500,000 | 5 | 75.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag11-il | 1,000,000 | 9 | 91.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag11-il | 1,000,000 | 5 | 91 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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