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AG09 (ag09-il)

AG09 - Drela AG09 airfoil


Airfoil ag09-il
Details Dat file Parser  
(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
Dat file parser warnings
  • Line 181 - X value too large but included: 1.000008 -0.000978
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Lednicer format dat file
Selig format dat file

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Polars for AG09 (ag09-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   ag09-il50,000932.4 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   ag09-il50,000532.9 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ag09-il100,000944.3 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ag09-il100,000544.1 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   ag09-il200,000956.4 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   ag09-il200,000555.6 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   ag09-il500,000974.4 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   ag09-il500,000570.7 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ag09-il1,000,000987 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   ag09-il1,000,000582 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
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