AG46ct -02f rot. (ag46ct02r-il)
AG46ct -02f rot. - Drela AG46ct -02f airfoil
| Details | Dat file | Parser | |
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(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)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ag46ct02r-il | 50,000 | 9 | 30.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag46ct02r-il | 50,000 | 5 | 33.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag46ct02r-il | 100,000 | 9 | 44.5 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag46ct02r-il | 100,000 | 5 | 44.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag46ct02r-il | 200,000 | 9 | 58.2 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag46ct02r-il | 200,000 | 5 | 55.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag46ct02r-il | 500,000 | 9 | 74.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag46ct02r-il | 500,000 | 5 | 72.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag46ct02r-il | 1,000,000 | 9 | 88.6 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag46ct02r-il | 1,000,000 | 5 | 86.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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