AG09 (ag09-il)
AG09 - Drela AG09 airfoil
| Details | Dat file | Parser | |
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(ag09-il) AG09 Drela AG09 airfoil Max thickness 4.9% at 17.4% chord. Max camber 1.8% at 34.1% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
AG09
0.999992 0.000975
0.994877 0.001385
0.984997 0.002172
0.973355 0.003092
0.961014 0.004063
0.948471 0.005040
0.935879 0.006015
0.923269 0.006985
0.910651 0.007947
0.898036 0.008902
0.885424 0.009849
0.872821 0.010788
0.860220 0.011722
0.847620 0.012646
0.835024 0.013562
0.822427 0.014472
0.809828 0.015375
0.797230 0.016271
0.784629 0.017166
0.772025 0.018056
0.759420 0.018939
0.746811 0.019821
0.734196 0.020693
0.721581 0.021557
0.708962 0.022412
0.696343 0.023256
0.683722 0.024092
0.671104 0.024916
0.658484 0.025729
0.645866 0.026533
0.633250 0.027319
0.620637 0.028093
0.608026 0.028857
0.595418 0.029603
0.582815 0.030336
0.570221 0.031052
0.557632 0.031752
0.545047 0.032436
0.532469 0.033100
0.519898 0.033745
0.507332 0.034374
0.494775 0.034981
0.482224 0.035568
0.469680 0.036132
0.457144 0.036679
0.444618 0.037202
0.432098 0.037702
0.419589 0.038180
0.407089 0.038634
0.394600 0.039065
0.382123 0.039467
0.369657 0.039844
0.357205 0.040190
0.344769 0.040506
0.332344 0.040789
0.319929 0.041039
0.307526 0.041250
0.295134 0.041422
0.282751 0.041550
0.270381 0.041629
0.258022 0.041657
0.245673 0.041630
0.233335 0.041543
0.221013 0.041387
0.208701 0.041159
0.196409 0.040852
0.184137 0.040456
0.171890 0.039962
0.159674 0.039360
0.147500 0.038639
0.135384 0.037786
0.123346 0.036781
0.111403 0.035611
0.099599 0.034258
0.087988 0.032707
0.076632 0.030940
0.065592 0.028941
0.054955 0.026698
0.044838 0.024209
0.035432 0.021503
0.027030 0.018665
0.019957 0.015852
0.014370 0.013236
0.010159 0.010920
0.007023 0.008900
0.004686 0.007130
0.002943 0.005557
0.001661 0.004136
0.000768 0.002826
0.000237 0.001596
0.000020 0.000469
0.000035 -0.000607
0.000304 -0.001744
0.000921 -0.002960
0.001983 -0.004197
0.003557 -0.005388
0.005705 -0.006536
0.008550 -0.007661
0.012325 -0.008776
0.017379 -0.009878
0.024064 -0.010898
0.032470 -0.011719
0.042286 -0.012262
0.053028 -0.012512
0.064326 -0.012513
0.075973 -0.012334
0.087860 -0.012019
0.099924 -0.011622
0.112115 -0.011164
0.124400 -0.010664
0.136759 -0.010143
0.149239 -0.009616
0.161806 -0.009087
0.174436 -0.008561
0.187120 -0.008044
0.199798 -0.007540
0.212512 -0.007052
0.225265 -0.006584
0.238067 -0.006138
0.250882 -0.005719
0.263744 -0.005324
0.276627 -0.004954
0.289536 -0.004608
0.302465 -0.004284
0.315394 -0.003983
0.328309 -0.003703
0.341200 -0.003444
0.354050 -0.003206
0.366854 -0.002987
0.379606 -0.002787
0.392309 -0.002605
0.404973 -0.002440
0.417637 -0.002289
0.430273 -0.002150
0.442893 -0.002022
0.455500 -0.001905
0.468094 -0.001797
0.480690 -0.001698
0.493281 -0.001608
0.505866 -0.001526
0.518446 -0.001451
0.531024 -0.001383
0.543599 -0.001322
0.556176 -0.001267
0.568753 -0.001218
0.581331 -0.001176
0.593912 -0.001140
0.606498 -0.001110
0.619084 -0.001086
0.631673 -0.001068
0.644262 -0.001057
0.656854 -0.001051
0.669498 -0.001048
0.682141 -0.001046
0.694788 -0.001043
0.707435 -0.001040
0.720082 -0.001038
0.732728 -0.001035
0.745373 -0.001032
0.758019 -0.001030
0.770665 -0.001027
0.783309 -0.001024
0.795954 -0.001022
0.808602 -0.001019
0.821252 -0.001016
0.833906 -0.001014
0.846566 -0.001011
0.859230 -0.001008
0.871902 -0.001005
0.884577 -0.001003
0.897247 -0.001000
0.909913 -0.000997
0.922581 -0.000995
0.935248 -0.000992
0.947912 -0.000989
0.960538 -0.000987
0.973004 -0.000984
0.984833 -0.000982
0.994850 -0.000980
1.000008 -0.000978
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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 AG09 (ag09-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ag09-il | 50,000 | 9 | 32.4 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag09-il | 50,000 | 5 | 32.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag09-il | 100,000 | 9 | 44.3 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag09-il | 100,000 | 5 | 44.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag09-il | 200,000 | 9 | 56.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag09-il | 200,000 | 5 | 55.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag09-il | 500,000 | 9 | 74.4 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag09-il | 500,000 | 5 | 70.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag09-il | 1,000,000 | 9 | 87 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag09-il | 1,000,000 | 5 | 82 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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