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AG45c -03f (ag45c03-il)

AG45c -03f - Drela AG45c -03f airfoil


Airfoil ag45c03-il
Details Dat file Parser  
(ag45c03-il) AG45c -03f
Drela AG45c -03f airfoil
Max thickness 6.9% at 23.5% chord.
Max camber 2% at 31.7% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
AG45c -03f
     1.000086    0.015922
     0.994138    0.016317
     0.982099    0.017150
     0.968507    0.018092
     0.954615    0.019018
     0.940684    0.019941
     0.926751    0.020852
     0.912817    0.021756
     0.898884    0.022651
     0.884954    0.023532
     0.871023    0.024397
     0.857096    0.025245
     0.843173    0.026073
     0.829250    0.026883
     0.815328    0.027672
     0.801405    0.028440
     0.787486    0.029188
     0.773565    0.029917
     0.759646    0.030627
     0.745726    0.031316
     0.731807    0.031988
     0.717884    0.032644
     0.707074    0.033141
     0.703460    0.033311
     0.701652    0.033395
     0.698206    0.033724
     0.691314    0.034394
     0.677446    0.035733
     0.663581    0.037053
     0.656762    0.037694
     0.646541    0.038646
     0.635857    0.039627
     0.621994    0.040879
     0.605869    0.042302
     0.594295    0.043299
     0.580476    0.044462
     0.566659    0.045596
     0.555673    0.046476
     0.546779    0.047173
     0.538810    0.047786
     0.524991    0.048822
     0.511176    0.049822
     0.497336    0.050788
     0.483480    0.051715
     0.469633    0.052602
     0.455797    0.053447
     0.441954    0.054250
     0.428114    0.055008
     0.414279    0.055721
     0.400440    0.056378
     0.386604    0.056967
     0.372772    0.057484
     0.358942    0.057929
     0.345111    0.058298
     0.331287    0.058589
     0.317470    0.058797
     0.303656    0.058914
     0.289853    0.058939
     0.276060    0.058864
     0.262271    0.058683
     0.248498    0.058389
     0.234746    0.057976
     0.221005    0.057435
     0.207291    0.056758
     0.193607    0.055937
     0.179951    0.054959
     0.166346    0.053814
     0.152785    0.052485
     0.139290    0.050958
     0.125875    0.049215
     0.112549    0.047231
     0.099355    0.044984
     0.086310    0.042435
     0.073476    0.039546
     0.060899    0.036264
     0.048706    0.032533
     0.037085    0.028314
     0.026424    0.023642
     0.017422    0.018794
     0.010776    0.014325
     0.006402    0.010622
     0.003629    0.007640
     0.001877    0.005178
     0.000830    0.003085
     0.000323    0.001304
     0.000250   -0.000178
     0.000581   -0.001543
     0.001479   -0.002917
     0.003095   -0.004214
     0.005482   -0.005487
     0.008963   -0.006839
     0.014198   -0.008345
     0.022017   -0.009970
     0.032333   -0.011478
     0.044204   -0.012670
     0.056845   -0.013515
     0.069853   -0.014071
     0.083076   -0.014399
     0.096446   -0.014558
     0.109914   -0.014581
     0.123457   -0.014492
     0.137057   -0.014307
     0.150705   -0.014041
     0.164384   -0.013707
     0.178099   -0.013314
     0.191835   -0.012872
     0.205592   -0.012389
     0.219378   -0.011885
     0.233198   -0.011374
     0.247042   -0.010859
     0.260919   -0.010338
     0.274829   -0.009811
     0.288770   -0.009279
     0.302739   -0.008743
     0.316729   -0.008203
     0.330733   -0.007659
     0.344757   -0.007112
     0.358791   -0.006561
     0.372833   -0.006009
     0.386891   -0.005453
     0.400968   -0.004895
     0.415056   -0.004335
     0.429138   -0.003775
     0.443210   -0.003214
     0.457270   -0.002653
     0.471326   -0.002091
     0.485372   -0.001531
     0.499404   -0.000971
     0.513429   -0.000412
     0.527448    0.000146
     0.541461    0.000703
     0.549029    0.001003
     0.558642    0.001383
     0.568957    0.001791
     0.582414    0.002321
     0.595587    0.002837
     0.609478    0.003380
     0.623073    0.003908
     0.636668    0.004433
     0.646250    0.004801
     0.655266    0.005147
     0.663866    0.005474
     0.677534    0.005992
     0.691197    0.006506
     0.697089    0.006727
     0.700090    0.006839
     0.706464    0.007075
     0.718992    0.007539
     0.732862    0.008047
     0.746721    0.008549
     0.760568    0.009047
     0.774417    0.009538
     0.788265    0.010023
     0.802117    0.010503
     0.815974    0.010977
     0.829832    0.011440
     0.843692    0.011882
     0.857561    0.012306
     0.871428    0.012708
     0.885297    0.013084
     0.899175    0.013445
     0.913051    0.013773
     0.926933    0.014076
     0.940816    0.014342
     0.954703    0.014571
     0.968566    0.014761
     0.982184    0.014890
     0.994208    0.014978
     1.000152    0.015029
Dat file parser warnings
  • Line 2 - X value too large but included: 1.000086 0.015922
  • Line 170 - X value too large but included: 1.000152 0.015029
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Polars for AG45c -03f (ag45c03-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   ag45c03-il50,000929.7 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   ag45c03-il50,000534.9 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ag45c03-il100,000946 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   ag45c03-il100,000547.9 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   ag45c03-il200,000962.4 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ag45c03-il200,000561 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   ag45c03-il500,000983 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   ag45c03-il500,000578.1 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   ag45c03-il1,000,000997.4 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   ag45c03-il1,000,000591.2 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
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