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FX 83-W-227 (fx83w227-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: FX 83-W-227 (fx83w227-il)
Reynolds number: 50,000
Max Cl/Cd: 6.96 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx83w227-il-50000-n5.txt
Download as CSV file: xf-fx83w227-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 83-W-227                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.000  -0.3809   0.14223   0.13460  -0.0523   1.0000   0.1175
 -13.750  -0.3909   0.13805   0.13045  -0.0533   0.9989   0.1192
 -13.250  -0.4458   0.11550   0.10784  -0.0675   0.9906   0.1236
 -13.000  -0.4084   0.11654   0.10884  -0.0684   0.9851   0.1257
 -12.750  -0.4015   0.11197   0.10423  -0.0721   0.9807   0.1283
 -12.500  -0.4720   0.09465   0.08682  -0.0812   0.9752   0.1313
 -12.250  -0.6151   0.07319   0.06486  -0.0914   0.9666   0.1315
 -12.000  -0.6548   0.06696   0.05829  -0.0930   0.9577   0.1328
 -11.750  -0.6838   0.06292   0.05392  -0.0921   0.9478   0.1342
 -11.500  -0.7057   0.05957   0.05017  -0.0908   0.9394   0.1360
 -11.250  -0.6960   0.05817   0.04876  -0.0901   0.9312   0.1385
 -11.000  -0.6749   0.05671   0.04725  -0.0912   0.9262   0.1419
 -10.750  -0.6819   0.05535   0.04574  -0.0880   0.9162   0.1442
 -10.500  -0.6791   0.05349   0.04359  -0.0868   0.9098   0.1477
 -10.250  -0.6944   0.05227   0.04210  -0.0818   0.8991   0.1499
 -10.000  -0.6659   0.05110   0.04096  -0.0831   0.8943   0.1541
  -9.750  -0.6571   0.05022   0.04003  -0.0811   0.8867   0.1577
  -9.500  -0.6480   0.04907   0.03869  -0.0794   0.8793   0.1619
  -9.250  -0.6244   0.04771   0.03714  -0.0800   0.8749   0.1675
  -9.000  -0.6205   0.04728   0.03674  -0.0768   0.8658   0.1712
  -8.750  -0.6011   0.04631   0.03565  -0.0764   0.8601   0.1771
  -8.500  -0.5719   0.04519   0.03440  -0.0775   0.8563   0.1844
  -8.250  -0.5741   0.04495   0.03419  -0.0732   0.8463   0.1885
  -8.000  -0.5529   0.04408   0.03314  -0.0728   0.8410   0.1965
  -7.750  -0.5201   0.04321   0.03233  -0.0743   0.8377   0.2055
  -7.500  -0.5274   0.04310   0.03217  -0.0690   0.8272   0.2107
  -7.250  -0.5031   0.04237   0.03141  -0.0690   0.8223   0.2203
  -7.000  -0.4744   0.04156   0.03049  -0.0697   0.8188   0.2330
  -6.750  -0.4837   0.04163   0.03066  -0.0641   0.8083   0.2385
  -6.500  -0.4626   0.04100   0.02996  -0.0634   0.8033   0.2519
  -6.250  -0.4347   0.04024   0.02926  -0.0638   0.7998   0.2677
  -6.000  -0.4473   0.04043   0.02951  -0.0577   0.7892   0.2749
  -5.750  -0.4289   0.03989   0.02901  -0.0565   0.7842   0.2921
  -5.500  -0.4034   0.03917   0.02837  -0.0563   0.7807   0.3140
  -5.250  -0.4174   0.03947   0.02869  -0.0501   0.7700   0.3255
  -5.000  -0.4002   0.03900   0.02835  -0.0485   0.7650   0.3492
  -4.750  -0.3755   0.03841   0.02789  -0.0480   0.7616   0.3793
  -4.500  -0.3886   0.03884   0.02841  -0.0418   0.7510   0.3955
  -4.250  -0.3706   0.03858   0.02827  -0.0401   0.7459   0.4273
  -4.000  -0.3445   0.03829   0.02809  -0.0394   0.7427   0.4636
  -3.750  -0.3546   0.03892   0.02882  -0.0337   0.7324   0.4839
  -3.500  -0.3350   0.03902   0.02900  -0.0319   0.7273   0.5153
  -3.250  -0.3066   0.03901   0.02901  -0.0313   0.7240   0.5481
  -3.000  -0.3134   0.03977   0.02980  -0.0261   0.7143   0.5678
  -2.750  -0.2954   0.04003   0.03003  -0.0242   0.7088   0.5941
  -2.500  -0.2691   0.04003   0.02996  -0.0232   0.7053   0.6212
  -2.250  -0.2722   0.04085   0.03077  -0.0187   0.6963   0.6390
  -2.000  -0.2570   0.04119   0.03105  -0.0164   0.6903   0.6609
  -1.750  -0.2281   0.04135   0.03117  -0.0157   0.6867   0.6828
  -1.500  -0.2257   0.04211   0.03191  -0.0120   0.6787   0.7005
  -1.250  -0.2107   0.04267   0.03244  -0.0098   0.6722   0.7186
  -1.000  -0.1813   0.04287   0.03258  -0.0093   0.6684   0.7379
  -0.750  -0.1450   0.04293   0.03257  -0.0098   0.6659   0.7565
  -0.500  -0.1589   0.04420   0.03387  -0.0046   0.6543   0.7710
  -0.250  -0.1311   0.04438   0.03397  -0.0042   0.6503   0.7884
   0.000  -0.0975   0.04432   0.03380  -0.0045   0.6476   0.8055
   0.250  -0.0995   0.04579   0.03531  -0.0014   0.6367   0.8181
   0.500  -0.0679   0.04609   0.03554  -0.0021   0.6323   0.8322
   0.750  -0.0322   0.04608   0.03544  -0.0031   0.6295   0.8467
   1.000  -0.0243   0.04767   0.03704  -0.0021   0.6196   0.8585
   1.250   0.0093   0.04816   0.03747  -0.0036   0.6146   0.8704
   1.500   0.0524   0.04832   0.03754  -0.0062   0.6115   0.8820
   2.000   0.0979   0.05064   0.03980  -0.0082   0.5969   0.9044
   2.250   0.1507   0.05097   0.04004  -0.0129   0.5936   0.9115
   2.500   0.1956   0.05090   0.03989  -0.0158   0.5912   0.9219
   2.750   0.2004   0.05353   0.04256  -0.0164   0.5793   0.9317
   3.000   0.2414   0.05377   0.04274  -0.0193   0.5756   0.9414
   3.250   0.2887   0.05371   0.04261  -0.0229   0.5731   0.9501
   3.500   0.2891   0.05649   0.04544  -0.0232   0.5614   0.9620
   3.750   0.3283   0.05684   0.04574  -0.0263   0.5575   0.9716
   4.000   0.3741   0.05677   0.04562  -0.0298   0.5550   0.9812
   4.500   0.4066   0.06025   0.04911  -0.0328   0.5396   1.0000
   4.750   0.4157   0.05974   0.04852  -0.0302   0.5368   1.0000
   5.000   0.3706   0.06219   0.05094  -0.0234   0.5255   1.0000
   5.250   0.3763   0.06232   0.05098  -0.0208   0.5211   1.0000
   5.500   0.3934   0.06214   0.05070  -0.0192   0.5184   1.0000
   5.750   0.3644   0.06506   0.05357  -0.0149   0.5079   1.0000
   6.000   0.3767   0.06559   0.05403  -0.0134   0.5033   1.0000
   6.250   0.3982   0.06568   0.05404  -0.0126   0.5005   1.0000
   6.500   0.3778   0.06871   0.05706  -0.0095   0.4908   1.0000
   6.750   0.3891   0.06970   0.05800  -0.0083   0.4861   1.0000
   7.000   0.4104   0.07001   0.05825  -0.0076   0.4830   1.0000
   7.500   0.4067   0.07415   0.06235  -0.0044   0.4690   1.0000
   7.750   0.4265   0.07475   0.06292  -0.0038   0.4656   1.0000
   8.000   0.4514   0.07500   0.06312  -0.0034   0.4633   1.0000
   8.250   0.4262   0.07905   0.06722  -0.0013   0.4524   1.0000
   8.500   0.4441   0.07990   0.06804  -0.0007   0.4486   1.0000
   8.750   0.4676   0.08034   0.06846  -0.0004   0.4460   1.0000
   9.000   0.4477   0.08427   0.07242   0.0011   0.4365   1.0000
   9.250   0.4621   0.08545   0.07360   0.0017   0.4319   1.0000
   9.500   0.4845   0.08603   0.07417   0.0020   0.4290   1.0000
   9.750   0.4743   0.08941   0.07759   0.0029   0.4215   1.0000
  10.000   0.4807   0.09132   0.07951   0.0035   0.4156   1.0000
  10.250   0.5009   0.09211   0.08030   0.0037   0.4121   1.0000
  10.500   0.5267   0.09244   0.08064   0.0040   0.4097   1.0000
  11.000   0.5176   0.09847   0.08675   0.0050   0.3956   1.0000
  11.250   0.5420   0.09893   0.08723   0.0052   0.3928   1.0000
  11.500   0.5238   0.10326   0.09161   0.0056   0.3839   1.0000
  11.750   0.5362   0.10484   0.09323   0.0058   0.3792   1.0000
  12.000   0.5586   0.10547   0.09388   0.0060   0.3759   1.0000
  12.250   0.5484   0.10916   0.09763   0.0061   0.3681   1.0000
  12.500   0.5565   0.11116   0.09967   0.0062   0.3626   1.0000
  12.750   0.5769   0.11200   0.10055   0.0063   0.3591   1.0000
  13.000   0.5741   0.11505   0.10365   0.0063   0.3523   1.0000
  13.250   0.5778   0.11748   0.10613   0.0062   0.3460   1.0000
  13.500   0.5968   0.11844   0.10714   0.0063   0.3423   1.0000
  14.000   0.5996   0.12382   0.11263   0.0059   0.3292   1.0000
  14.250   0.6186   0.12473   0.11359   0.0060   0.3253   1.0000
  14.750   0.6224   0.13006   0.11904   0.0054   0.3121   1.0000
  15.000   0.6420   0.13086   0.11990   0.0054   0.3082   1.0000
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