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AG45ct -02f (ag45ct02r-il)

AG45ct -02f - Drela AG45ct -02f airfoil


Airfoil ag45ct02r-il
Details Dat file Parser  
(ag45ct02r-il) AG45ct -02f
Drela AG45ct -02f airfoil
Max thickness 6.9% at 23.3% chord.
Max camber 1.8% at 33.1% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
AG45ct -02f
     1.000000    0.000311
     0.994227    0.000847
     0.982595    0.001929
     0.969434    0.003139
     0.956049    0.004355
     0.942645    0.005557
     0.929204    0.006747
     0.915742    0.007922
     0.902251    0.009085
     0.888763    0.010232
     0.875271    0.011366
     0.861775    0.012483
     0.848292    0.013586
     0.834812    0.014671
     0.821351    0.015742
     0.807898    0.016797
     0.794449    0.017838
     0.781009    0.018863
     0.767570    0.019874
     0.754139    0.020871
     0.740701    0.021854
     0.727245    0.022823
     0.716793    0.023568
     0.710626    0.024002
     0.707082    0.024251
     0.702553    0.024571
     0.697239    0.025118
     0.686613    0.026207
     0.672246    0.027662
     0.665190    0.028368
     0.654607    0.029418
     0.643558    0.030500
     0.629239    0.031878
     0.612612    0.033445
     0.600711    0.034541
     0.586534    0.035819
     0.572386    0.037063
     0.561159    0.038028
     0.552085    0.038789
     0.543968    0.039459
     0.529917    0.040590
     0.515878    0.041683
     0.501782    0.042740
     0.487635    0.043762
     0.473459    0.044743
     0.459248    0.045684
     0.444998    0.046580
     0.430752    0.047427
     0.416527    0.048221
     0.402335    0.048957
     0.388199    0.049631
     0.374125    0.050243
     0.360112    0.050788
     0.346152    0.051266
     0.332237    0.051674
     0.318350    0.052011
     0.304472    0.052274
     0.290601    0.052459
     0.276746    0.052560
     0.262911    0.052567
     0.249109    0.052477
     0.235341    0.052278
     0.221593    0.051963
     0.207871    0.051520
     0.194176    0.050937
     0.180507    0.050204
     0.166888    0.049307
     0.153309    0.048233
     0.139793    0.046967
     0.126354    0.045491
     0.113001    0.043780
     0.099775    0.041815
     0.086695    0.039554
     0.073820    0.036962
     0.061195    0.033986
     0.048949    0.030569
     0.037266    0.026672
     0.026537    0.022321
     0.017464    0.017772
     0.010753    0.013553
     0.006324    0.010038
     0.003508    0.007194
     0.001719    0.004837
     0.000641    0.002824
     0.000108    0.001102
     0.000012   -0.000341
     0.000323   -0.001724
     0.001200   -0.003122
     0.002797   -0.004458
     0.005165   -0.005785
     0.008624   -0.007213
     0.013835   -0.008829
     0.021627   -0.010619
     0.031916   -0.012345
     0.043766   -0.013786
     0.056391   -0.014905
     0.069386   -0.015756
     0.082602   -0.016393
     0.095968   -0.016868
     0.109435   -0.017200
     0.122981   -0.017412
     0.136584   -0.017525
     0.150238   -0.017559
     0.163923   -0.017527
     0.177645   -0.017443
     0.191390   -0.017314
     0.205156   -0.017148
     0.218951   -0.016951
     0.232789   -0.016727
     0.246662   -0.016479
     0.260584   -0.016211
     0.274554   -0.015926
     0.288570   -0.015627
     0.302626   -0.015315
     0.316706   -0.014990
     0.330800   -0.014657
     0.344916   -0.014315
     0.359042   -0.013965
     0.373168   -0.013610
     0.387310   -0.013247
     0.401465   -0.012878
     0.415627   -0.012504
     0.429771   -0.012126
     0.443898   -0.011743
     0.458005   -0.011357
     0.472101   -0.010967
     0.486182   -0.010574
     0.500232   -0.010178
     0.514274   -0.009778
     0.528296   -0.009379
     0.542309   -0.008976
     0.549868   -0.008761
     0.559467   -0.008487
     0.569774   -0.008195
     0.583198   -0.007814
     0.596337   -0.007448
     0.610185   -0.007068
     0.623741   -0.006703
     0.637286   -0.006344
     0.646835   -0.006099
     0.655828   -0.005869
     0.664399   -0.005656
     0.678037   -0.005317
     0.691677   -0.004993
     0.697217   -0.004864
     0.699989   -0.004799
     0.702621   -0.004742
     0.706923   -0.004644
     0.719461   -0.004368
     0.733337   -0.004070
     0.747215   -0.003781
     0.761077   -0.003501
     0.774940   -0.003231
     0.788815   -0.002969
     0.802688   -0.002719
     0.816585   -0.002478
     0.830472   -0.002249
     0.844343   -0.002030
     0.858214   -0.001824
     0.872063   -0.001626
     0.885892   -0.001441
     0.899731   -0.001266
     0.913535   -0.001102
     0.927344   -0.000948
     0.941134   -0.000804
     0.954910   -0.000674
     0.968662   -0.000551
     0.982162   -0.000441
     0.994091   -0.000353
     1.000000   -0.000311
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Polars for AG45ct -02f (ag45ct02r-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   ag45ct02r-il50,000930.3 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   ag45ct02r-il50,000534.3 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   ag45ct02r-il100,000945.3 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ag45ct02r-il100,000546.8 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   ag45ct02r-il200,000960.6 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ag45ct02r-il200,000559.4 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ag45ct02r-il500,000980.5 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ag45ct02r-il500,000576.1 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   ag45ct02r-il1,000,000994.6 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ag45ct02r-il1,000,000589.1 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
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