AG44ct -02f (ag44ct02r-il)
AG44ct -02f - Drela AG44ct -02f airfoil
| Details | Dat file | Parser | |
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(ag44ct02r-il) AG44ct -02f Drela AG44ct -02f airfoil Max thickness 7.3% at 24.6% chord. Max camber 1.9% at 34.4% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
AG44ct -02f
1.000000 0.000267
0.994281 0.000879
0.982676 0.002150
0.969470 0.003565
0.955940 0.004992
0.942320 0.006398
0.928654 0.007795
0.914956 0.009178
0.901209 0.010535
0.887436 0.011874
0.873633 0.013196
0.859806 0.014491
0.845970 0.015768
0.832112 0.017031
0.818240 0.018273
0.804360 0.019491
0.790481 0.020688
0.776591 0.021864
0.762700 0.023012
0.748809 0.024141
0.734918 0.025241
0.721029 0.026318
0.710013 0.027153
0.705317 0.027503
0.702970 0.027676
0.700066 0.027993
0.694517 0.028595
0.680299 0.030110
0.666102 0.031598
0.658803 0.032350
0.648461 0.033403
0.637773 0.034475
0.623647 0.035861
0.611708 0.037009
0.595495 0.038529
0.581500 0.039804
0.567540 0.041038
0.556456 0.041995
0.547499 0.042746
0.539476 0.043405
0.525583 0.044513
0.511713 0.045572
0.497828 0.046587
0.483928 0.047556
0.470018 0.048477
0.456103 0.049351
0.442153 0.050176
0.428184 0.050950
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0.400162 0.052340
0.386128 0.052949
0.372097 0.053500
0.358076 0.053987
0.344066 0.054410
0.330081 0.054761
0.316128 0.055041
0.302204 0.055242
0.288319 0.055361
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0.260641 0.055332
0.246839 0.055170
0.233052 0.054899
0.219271 0.054508
0.205517 0.053989
0.191796 0.053328
0.178103 0.052512
0.164466 0.051528
0.150878 0.050355
0.137362 0.048975
0.123932 0.047367
0.110603 0.045501
0.097421 0.043352
0.084406 0.040882
0.071626 0.038057
0.059136 0.034822
0.047069 0.031135
0.035622 0.026972
0.025185 0.022385
0.016439 0.017663
0.010036 0.013355
0.005852 0.009820
0.003217 0.006995
0.001562 0.004682
0.000576 0.002724
0.000097 0.001065
0.000010 -0.000322
0.000274 -0.001626
0.001049 -0.003004
0.002544 -0.004375
0.004836 -0.005752
0.008219 -0.007245
0.013354 -0.008947
0.021069 -0.010854
0.031305 -0.012714
0.043126 -0.014293
0.055741 -0.015540
0.068738 -0.016492
0.081966 -0.017214
0.095344 -0.017757
0.108825 -0.018149
0.122384 -0.018416
0.136003 -0.018579
0.149669 -0.018653
0.163367 -0.018658
0.177102 -0.018606
0.190859 -0.018505
0.204643 -0.018363
0.218459 -0.018185
0.232295 -0.017977
0.246151 -0.017743
0.260037 -0.017486
0.273949 -0.017208
0.287888 -0.016910
0.301851 -0.016598
0.315837 -0.016268
0.329834 -0.015924
0.343848 -0.015567
0.357872 -0.015199
0.371905 -0.014822
0.385973 -0.014434
0.400091 -0.014039
0.414239 -0.013636
0.428406 -0.013226
0.442567 -0.012812
0.456733 -0.012394
0.470889 -0.011974
0.485027 -0.011551
0.499146 -0.011128
0.513244 -0.010706
0.527306 -0.010285
0.541344 -0.009866
0.548916 -0.009641
0.558519 -0.009356
0.568815 -0.009052
0.582218 -0.008660
0.595591 -0.008271
0.601918 -0.008088
0.609169 -0.007881
0.622761 -0.007496
0.636337 -0.007118
0.646235 -0.006845
0.655333 -0.006599
0.663619 -0.006375
0.677270 -0.006014
0.690933 -0.005662
0.697066 -0.005506
0.700447 -0.005422
0.706337 -0.005275
0.718625 -0.004975
0.732538 -0.004643
0.746458 -0.004323
0.760376 -0.004015
0.774309 -0.003718
0.788213 -0.003434
0.802087 -0.003163
0.815969 -0.002906
0.829825 -0.002663
0.843705 -0.002431
0.857569 -0.002206
0.871411 -0.001986
0.885253 -0.001775
0.899129 -0.001568
0.912961 -0.001370
0.926824 -0.001177
0.940687 -0.000991
0.954562 -0.000811
0.968423 -0.000638
0.982034 -0.000474
0.994042 -0.000335
1.000000 -0.000267
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Polars for AG44ct -02f (ag44ct02r-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ag44ct02r-il | 50,000 | 9 | 30.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag44ct02r-il | 50,000 | 5 | 34.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag44ct02r-il | 100,000 | 9 | 45.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag44ct02r-il | 100,000 | 5 | 47.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag44ct02r-il | 200,000 | 9 | 61.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag44ct02r-il | 200,000 | 5 | 60.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag44ct02r-il | 500,000 | 9 | 82.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag44ct02r-il | 500,000 | 5 | 78.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag44ct02r-il | 1,000,000 | 9 | 97.2 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag44ct02r-il | 1,000,000 | 5 | 91.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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