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AG47ct -02f rot. (ag47ct02r-il)

AG47ct -02f rot. - Drela AG47ct -02f airfoil


Airfoil ag47ct02r-il
Details Dat file Parser  
(ag47ct02r-il) AG47ct -02f rot.
Drela AG47ct -02f airfoil
Max thickness 5% at 22.5% chord.
Max camber 1.2% at 33.4% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
AG47ct  -02f rot.
     1.000000    0.000298
     0.994152    0.000709
     0.982302    0.001537
     0.968889    0.002440
     0.955155    0.003356
     0.941367    0.004260
     0.927559    0.005152
     0.913746    0.006024
     0.899930    0.006873
     0.886134    0.007708
     0.872342    0.008521
     0.858556    0.009309
     0.844773    0.010088
     0.830993    0.010845
     0.817215    0.011582
     0.803444    0.012303
     0.789675    0.013005
     0.775912    0.013693
     0.762154    0.014360
     0.748397    0.015011
     0.734651    0.015647
     0.720906    0.016262
     0.708714    0.016794
     0.703752    0.017006
     0.701271    0.017110
     0.698942    0.017290
     0.694281    0.017652
     0.680252    0.018712
     0.666241    0.019757
     0.652253    0.020777
     0.638276    0.021777
     0.624319    0.022753
     0.612512    0.023564
     0.605008    0.024070
     0.601913    0.024278
     0.595187    0.024723
     0.582617    0.025541
     0.568776    0.026420
     0.557785    0.027099
     0.548895    0.027638
     0.540934    0.028112
     0.527144    0.028911
     0.513375    0.029684
     0.499597    0.030427
     0.485812    0.031143
     0.472036    0.031827
     0.458272    0.032479
     0.444503    0.033101
     0.430738    0.033689
     0.416978    0.034242
     0.403216    0.034759
     0.389456    0.035238
     0.375704    0.035675
     0.361956    0.036073
     0.348208    0.036428
     0.334468    0.036736
     0.320736    0.036998
     0.307008    0.037209
     0.293291    0.037370
     0.279585    0.037476
     0.265881    0.037525
     0.252191    0.037515
     0.238519    0.037444
     0.224854    0.037305
     0.211211    0.037096
     0.197591    0.036811
     0.183991    0.036440
     0.170429    0.035978
     0.156899    0.035413
     0.143417    0.034734
     0.129995    0.033925
     0.116636    0.032969
     0.103377    0.031843
     0.090227    0.030520
     0.077240    0.028968
     0.064445    0.027139
     0.051951    0.024974
     0.039929    0.022391
     0.028756    0.019351
     0.019178    0.015963
     0.011961    0.012593
     0.007092    0.009596
     0.003938    0.007027
     0.001920    0.004778
     0.000715    0.002774
     0.000115    0.001027
     0.000017   -0.000447
     0.000386   -0.001800
     0.001370   -0.003115
     0.003057   -0.004323
     0.005493   -0.005498
     0.009022   -0.006721
     0.014303   -0.008052
     0.022165   -0.009445
     0.032509   -0.010718
     0.044393   -0.011712
     0.057033   -0.012425
     0.070035   -0.012920
     0.083249   -0.013246
     0.096611   -0.013444
     0.110069   -0.013546
     0.123602   -0.013577
     0.137192   -0.013552
     0.150832   -0.013482
     0.164509   -0.013374
     0.178233   -0.013237
     0.191981   -0.013074
     0.205756   -0.012889
     0.219555   -0.012690
     0.233369   -0.012473
     0.247197   -0.012246
     0.261043   -0.012006
     0.274904   -0.011760
     0.288782   -0.011506
     0.302677   -0.011247
     0.316587   -0.010982
     0.330510   -0.010716
     0.344449   -0.010445
     0.358402   -0.010173
     0.372366   -0.009897
     0.386349   -0.009621
     0.400359   -0.009343
     0.414383   -0.009065
     0.428405   -0.008786
     0.442423   -0.008508
     0.456437   -0.008231
     0.470449   -0.007955
     0.484454   -0.007678
     0.498456   -0.007404
     0.512456   -0.007130
     0.526459   -0.006856
     0.540456   -0.006584
     0.548018   -0.006437
     0.557624   -0.006255
     0.567937   -0.006055
     0.581396   -0.005801
     0.594367   -0.005554
     0.600854   -0.005432
     0.603423   -0.005384
     0.608560   -0.005287
     0.622259   -0.005031
     0.635956   -0.004780
     0.649639   -0.004532
     0.663321   -0.004289
     0.676995   -0.004047
     0.690661   -0.003809
     0.696821   -0.003706
     0.699977   -0.003653
     0.706136   -0.003552
     0.718449   -0.003345
     0.732355   -0.003119
     0.746251   -0.002897
     0.760142   -0.002683
     0.774029   -0.002474
     0.787918   -0.002273
     0.801809   -0.002079
     0.815709   -0.001893
     0.829601   -0.001715
     0.843491   -0.001544
     0.857392   -0.001382
     0.871281   -0.001232
     0.885171   -0.001086
     0.899062   -0.000948
     0.912944   -0.000823
     0.926831   -0.000710
     0.940709   -0.000605
     0.954584   -0.000505
     0.968438   -0.000421
     0.982044   -0.000389
     0.994060   -0.000389
     1.000000   -0.000395
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Polars for AG47ct -02f rot. (ag47ct02r-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   ag47ct02r-il50,000930.5 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ag47ct02r-il50,000530.3 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ag47ct02r-il100,000941.9 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   ag47ct02r-il100,000538.9 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   ag47ct02r-il200,000952.1 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ag47ct02r-il200,000549.6 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   ag47ct02r-il500,000965.4 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   ag47ct02r-il500,000566.7 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ag47ct02r-il1,000,000980.8 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   ag47ct02r-il1,000,000580.9 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
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