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AG46ct -02f rot. (ag46ct02r-il)

AG46ct -02f rot. - Drela AG46ct -02f airfoil


Airfoil ag46ct02r-il
Details Dat file Parser  
(ag46ct02r-il) AG46ct -02f rot.
Drela AG46ct -02f airfoil
Max thickness 6.1% at 23.3% chord.
Max camber 1.6% at 33% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
AG46ct  -02f rot.
     1.000000    0.000346
     0.994169    0.000862
     0.982335    0.001905
     0.968927    0.003065
     0.955241    0.004226
     0.941475    0.005371
     0.927672    0.006496
     0.913853    0.007600
     0.900020    0.008680
     0.886186    0.009739
     0.872347    0.010776
     0.858510    0.011788
     0.844677    0.012779
     0.830839    0.013749
     0.817007    0.014695
     0.803169    0.015620
     0.789339    0.016523
     0.775505    0.017405
     0.761673    0.018265
     0.747845    0.019103
     0.734023    0.019921
     0.720202    0.020716
     0.709236    0.021333
     0.704334    0.021605
     0.701884    0.021743
     0.699119    0.021987
     0.693594    0.022480
     0.679440    0.023729
     0.665306    0.024954
     0.658040    0.025575
     0.647741    0.026447
     0.637094    0.027336
     0.623018    0.028492
     0.611117    0.029454
     0.594940    0.030738
     0.580968    0.031826
     0.567026    0.032890
     0.555953    0.033722
     0.547001    0.034385
     0.538987    0.034973
     0.525105    0.035974
     0.511251    0.036955
     0.497391    0.037916
     0.483526    0.038847
     0.469666    0.039735
     0.455819    0.040579
     0.441963    0.041381
     0.428112    0.042135
     0.414265    0.042842
     0.400411    0.043499
     0.386560    0.044105
     0.372715    0.044656
     0.358875    0.045152
     0.345033    0.045590
     0.331198    0.045966
     0.317373    0.046276
     0.303549    0.046519
     0.289739    0.046688
     0.275939    0.046778
     0.262144    0.046788
     0.248365    0.046710
     0.234607    0.046538
     0.220861    0.046268
     0.207142    0.045890
     0.193452    0.045398
     0.179790    0.044783
     0.166180    0.044034
     0.152611    0.043139
     0.139108    0.042085
     0.125681    0.040856
     0.112342    0.039429
     0.099133    0.037784
     0.086069    0.035883
     0.073215    0.033687
     0.060617    0.031138
     0.048403    0.028169
     0.036770    0.024730
     0.026109    0.020827
     0.017121    0.016679
     0.010502    0.012773
     0.006152    0.009481
     0.003397    0.006797
     0.001658    0.004559
     0.000615    0.002642
     0.000104    0.000999
     0.000012   -0.000384
     0.000309   -0.001678
     0.001165   -0.003004
     0.002740   -0.004281
     0.005096   -0.005537
     0.008541   -0.006867
     0.013739   -0.008350
     0.021514   -0.009958
     0.031796   -0.011488
     0.043644   -0.012748
     0.056274   -0.013703
     0.069277   -0.014397
     0.082503   -0.014889
     0.095878   -0.015227
     0.109354   -0.015438
     0.122905   -0.015547
     0.136515   -0.015569
     0.150172   -0.015521
     0.163860   -0.015416
     0.177585   -0.015264
     0.191331   -0.015074
     0.205104   -0.014851
     0.218909   -0.014602
     0.232736   -0.014332
     0.246582   -0.014047
     0.260458   -0.013752
     0.274361   -0.013452
     0.288290   -0.013146
     0.302243   -0.012836
     0.316220   -0.012524
     0.330209   -0.012210
     0.344214   -0.011895
     0.358231   -0.011580
     0.372256   -0.011272
     0.386298   -0.010965
     0.400359   -0.010657
     0.414429   -0.010356
     0.428491   -0.010057
     0.442544   -0.009766
     0.456582   -0.009476
     0.470611   -0.009188
     0.484625   -0.008897
     0.498622   -0.008604
     0.512614   -0.008314
     0.526588   -0.008023
     0.540550   -0.007731
     0.548091   -0.007574
     0.557667   -0.007372
     0.567946   -0.007156
     0.581355   -0.006876
     0.594754   -0.006594
     0.601098   -0.006462
     0.608373   -0.006310
     0.622034   -0.006023
     0.635696   -0.005738
     0.645649   -0.005530
     0.654802   -0.005340
     0.663147   -0.005166
     0.676887   -0.004882
     0.690630   -0.004597
     0.696798   -0.004471
     0.699994   -0.004407
     0.702034   -0.004367
     0.706114   -0.004282
     0.718453   -0.004030
     0.732391   -0.003748
     0.746320   -0.003465
     0.760234   -0.003188
     0.774134   -0.002911
     0.788014   -0.002637
     0.801884   -0.002366
     0.815752   -0.002098
     0.829621   -0.001839
     0.843490   -0.001599
     0.857366   -0.001371
     0.871242   -0.001164
     0.885118   -0.000972
     0.899000   -0.000809
     0.912885   -0.000669
     0.926769   -0.000552
     0.940657   -0.000467
     0.954547   -0.000414
     0.968412   -0.000390
     0.982030   -0.000403
     0.994055   -0.000423
     1.000000   -0.000447
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Polars for AG46ct -02f rot. (ag46ct02r-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   ag46ct02r-il50,000930.8 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   ag46ct02r-il50,000533.3 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   ag46ct02r-il100,000944.5 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   ag46ct02r-il100,000544.4 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   ag46ct02r-il200,000958.2 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ag46ct02r-il200,000555.7 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   ag46ct02r-il500,000974.9 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ag46ct02r-il500,000572.5 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   ag46ct02r-il1,000,000988.6 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   ag46ct02r-il1,000,000586.2 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
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