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AG44ct -02f (ag44ct02r-il)

AG44ct -02f - Drela AG44ct -02f airfoil


Airfoil ag44ct02r-il
Details Dat file Parser  
(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
     0.414186    0.051671
     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
     0.274469    0.055394
     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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Lednicer format dat file
Selig format dat file

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Polars for AG44ct -02f (ag44ct02r-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   ag44ct02r-il50,000930.6 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ag44ct02r-il50,000534.6 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ag44ct02r-il100,000945.7 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   ag44ct02r-il100,000547.4 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ag44ct02r-il200,000961.2 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   ag44ct02r-il200,000560.6 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ag44ct02r-il500,000982.1 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   ag44ct02r-il500,000578.2 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ag44ct02r-il1,000,000997.2 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ag44ct02r-il1,000,000591.4 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
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