AG46c -03f (ag46c03-il)
AG46c -03f - Drela AG46c -03f airfoil
| Details | Dat file | Parser | |
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(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
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Polars for AG46c -03f (ag46c03-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ag46c03-il | 50,000 | 9 | 30.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag46c03-il | 50,000 | 5 | 33.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag46c03-il | 100,000 | 9 | 44.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag46c03-il | 100,000 | 5 | 44.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag46c03-il | 200,000 | 9 | 58.1 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag46c03-il | 200,000 | 5 | 55.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag46c03-il | 500,000 | 9 | 74.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag46c03-il | 500,000 | 5 | 72.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag46c03-il | 1,000,000 | 9 | 88.5 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag46c03-il | 1,000,000 | 5 | 86 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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