AG47ct -02f rot. (ag47ct02r-il)
AG47ct -02f rot. - Drela AG47ct -02f airfoil
| Details | Dat file | Parser | |
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(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)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ag47ct02r-il | 50,000 | 9 | 30.5 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag47ct02r-il | 50,000 | 5 | 30.3 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag47ct02r-il | 100,000 | 9 | 41.9 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag47ct02r-il | 100,000 | 5 | 38.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag47ct02r-il | 200,000 | 9 | 52.1 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag47ct02r-il | 200,000 | 5 | 49.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag47ct02r-il | 500,000 | 9 | 65.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag47ct02r-il | 500,000 | 5 | 66.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag47ct02r-il | 1,000,000 | 9 | 80.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag47ct02r-il | 1,000,000 | 5 | 80.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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