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AG46c -03f (ag46c03-il)

AG46c -03f - Drela AG46c -03f airfoil


Airfoil ag46c03-il
Details Dat file Parser  
(ag46c03-il) AG46c -03f
Drela AG46c -03f airfoil
Max thickness 6% at 23.3% chord.
Max camber 1.9% at 37.3% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
AG46c -03f
     1.000090    0.015848
     0.994142    0.016169
     0.982105    0.016880
     0.968515    0.017692
     0.954624    0.018494
     0.940696    0.019304
     0.926766    0.020115
     0.912837    0.020917
     0.898906    0.021707
     0.884978    0.022482
     0.871047    0.023240
     0.857123    0.023982
     0.843198    0.024703
     0.829276    0.025411
     0.815353    0.026096
     0.801427    0.026764
     0.787506    0.027412
     0.773584    0.028043
     0.759661    0.028653
     0.745739    0.029242
     0.731816    0.029808
     0.717890    0.030352
     0.706832    0.030764
     0.703136    0.030904
     0.701288    0.030971
     0.697919    0.031263
     0.691180    0.031853
     0.677300    0.033049
     0.663422    0.034217
     0.656278    0.034806
     0.651965    0.035167
     0.646148    0.035630
     0.635666    0.036467
     0.621787    0.037546
     0.610035    0.038435
     0.594041    0.039610
     0.580199    0.040589
     0.566365    0.041533
     0.555362    0.042259
     0.546455    0.042829
     0.538476    0.043329
     0.524636    0.044165
     0.510800    0.044961
     0.496939    0.045721
     0.483062    0.046440
     0.469192    0.047116
     0.455335    0.047748
     0.441470    0.048338
     0.427610    0.048880
     0.413755    0.049376
     0.399894    0.049821
     0.386037    0.050215
     0.372187    0.050554
     0.358341    0.050839
     0.344495    0.051065
     0.330658    0.051229
     0.316830    0.051328
     0.303006    0.051359
     0.289197    0.051317
     0.275398    0.051197
     0.261605    0.050996
     0.247831    0.050707
     0.234078    0.050325
     0.220339    0.049844
     0.206629    0.049257
     0.192950    0.048556
     0.179300    0.047732
     0.165703    0.046775
     0.152152    0.045673
     0.138667    0.044413
     0.125262    0.042979
     0.111948    0.041349
     0.098766    0.039502
     0.085735    0.037402
     0.072916    0.035010
     0.060360    0.032269
     0.048194    0.029114
     0.036616    0.025498
     0.026016    0.021433
     0.017095    0.017148
     0.010536    0.013142
     0.006238    0.009784
     0.003524    0.007058
     0.001820    0.004794
     0.000806    0.002861
     0.000320    0.001211
     0.000249   -0.000173
     0.000568   -0.001462
     0.001444   -0.002774
     0.003038   -0.004026
     0.005412   -0.005244
     0.008878   -0.006518
     0.014099   -0.007911
     0.021901   -0.009375
     0.032206   -0.010701
     0.044072   -0.011717
     0.056713   -0.012409
     0.069722   -0.012838
     0.082949   -0.013064
     0.096323   -0.013136
     0.109795   -0.013086
     0.123342   -0.012938
     0.136945   -0.012713
     0.150596   -0.012425
     0.164277   -0.012085
     0.177995   -0.011702
     0.191733   -0.011285
     0.205499   -0.010850
     0.219297   -0.010409
     0.233118   -0.009964
     0.246958   -0.009513
     0.260828   -0.009058
     0.274725   -0.008598
     0.288648   -0.008133
     0.302596   -0.007663
     0.316566   -0.007190
     0.330550   -0.006713
     0.344548   -0.006232
     0.358560   -0.005747
     0.372579   -0.005260
     0.386614   -0.004769
     0.400668   -0.004276
     0.414731   -0.003779
     0.428787   -0.003281
     0.442832   -0.002781
     0.456863   -0.002280
     0.470885   -0.001778
     0.484891   -0.001275
     0.498881   -0.000771
     0.512865   -0.000267
     0.526832    0.000238
     0.540786    0.000743
     0.548323    0.001016
     0.557895    0.001363
     0.568168    0.001736
     0.581570    0.002222
     0.594962    0.002708
     0.601303    0.002937
     0.608574    0.003201
     0.622228    0.003696
     0.635882    0.004190
     0.645830    0.004550
     0.650807    0.004730
     0.654978    0.004880
     0.663319    0.005181
     0.677052    0.005676
     0.690787    0.006170
     0.696952    0.006391
     0.700094    0.006503
     0.706384    0.006729
     0.718717    0.007170
     0.732647    0.007665
     0.746569    0.008160
     0.760475    0.008651
     0.774369    0.009140
     0.788242    0.009626
     0.802105    0.010109
     0.815966    0.010589
     0.829827    0.011060
     0.843690    0.011511
     0.857560    0.011951
     0.871430    0.012370
     0.885300    0.012774
     0.899177    0.013149
     0.913056    0.013502
     0.926936    0.013831
     0.940820    0.014128
     0.954706    0.014394
     0.968568    0.014630
     0.982183    0.014824
     0.994205    0.014989
     1.000151    0.015055
Dat file parser warnings
  • Line 2 - X value too large but included: 1.000090 0.015848
  • Line 173 - X value too large but included: 1.000151 0.015055
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Polars for AG46c -03f (ag46c03-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   ag46c03-il50,000930.8 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   ag46c03-il50,000533.3 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ag46c03-il100,000944.5 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ag46c03-il100,000544.2 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ag46c03-il200,000958.1 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ag46c03-il200,000555.6 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   ag46c03-il500,000974.6 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ag46c03-il500,000572.5 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
   ag46c03-il1,000,000988.5 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   ag46c03-il1,000,000586 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
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