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FX 83-W-227 (fx83w227-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: FX 83-W-227 (fx83w227-il)
Reynolds number: 100,000
Max Cl/Cd: 31.29 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx83w227-il-100000-n5.txt
Download as CSV file: xf-fx83w227-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -16.000  -0.6944   0.08376   0.07737  -0.0911   1.0000   0.0808
 -15.750  -0.7565   0.07518   0.06851  -0.0930   1.0000   0.0810
 -15.500  -0.7775   0.07011   0.06326  -0.0952   0.9980   0.0818
 -15.250  -0.7569   0.06822   0.06139  -0.0978   0.9942   0.0831
 -15.000  -0.7517   0.06485   0.05790  -0.1008   0.9896   0.0844
 -14.750  -0.7509   0.06118   0.05406  -0.1039   0.9847   0.0858
 -14.500  -0.7518   0.05751   0.05016  -0.1067   0.9797   0.0872
 -14.250  -0.7545   0.05405   0.04642  -0.1087   0.9731   0.0888
 -14.000  -0.7556   0.05081   0.04285  -0.1105   0.9670   0.0904
 -13.750  -0.7353   0.04948   0.04157  -0.1116   0.9610   0.0919
 -13.500  -0.7146   0.04792   0.03997  -0.1136   0.9568   0.0937
 -13.250  -0.7047   0.04627   0.03822  -0.1139   0.9488   0.0954
 -13.000  -0.6903   0.04439   0.03615  -0.1153   0.9435   0.0978
 -12.750  -0.6818   0.04266   0.03418  -0.1153   0.9358   0.0998
 -12.500  -0.6609   0.04135   0.03285  -0.1162   0.9301   0.1019
 -12.250  -0.6352   0.04011   0.03160  -0.1180   0.9265   0.1043
 -12.000  -0.6239   0.03904   0.03044  -0.1172   0.9176   0.1066
 -11.750  -0.6033   0.03771   0.02894  -0.1181   0.9126   0.1097
 -11.500  -0.5748   0.03642   0.02754  -0.1201   0.9094   0.1127
 -11.250  -0.5631   0.03566   0.02679  -0.1187   0.8998   0.1150
 -11.000  -0.5376   0.03461   0.02567  -0.1199   0.8951   0.1185
 -10.750  -0.5109   0.03351   0.02439  -0.1213   0.8912   0.1227
 -10.500  -0.4989   0.03283   0.02373  -0.1196   0.8817   0.1255
 -10.250  -0.4729   0.03191   0.02278  -0.1206   0.8769   0.1295
 -10.000  -0.4516   0.03111   0.02188  -0.1206   0.8709   0.1340
  -9.750  -0.4360   0.03045   0.02117  -0.1194   0.8629   0.1380
  -9.500  -0.4100   0.02961   0.02032  -0.1202   0.8582   0.1428
  -9.250  -0.3938   0.02902   0.01965  -0.1191   0.8509   0.1479
  -9.000  -0.3773   0.02841   0.01903  -0.1179   0.8436   0.1530
  -8.750  -0.3520   0.02765   0.01824  -0.1184   0.8389   0.1592
  -8.500  -0.3416   0.02729   0.01778  -0.1159   0.8307   0.1650
  -8.250  -0.3267   0.02672   0.01726  -0.1144   0.8238   0.1709
  -8.000  -0.3011   0.02605   0.01652  -0.1146   0.8193   0.1797
  -7.750  -0.2996   0.02583   0.01631  -0.1104   0.8104   0.1851
  -7.500  -0.2851   0.02536   0.01584  -0.1086   0.8041   0.1933
  -7.250  -0.2618   0.02474   0.01520  -0.1083   0.7997   0.2036
  -7.000  -0.2674   0.02472   0.01520  -0.1025   0.7904   0.2101
  -6.750  -0.2534   0.02432   0.01479  -0.1004   0.7845   0.2208
  -6.500  -0.2298   0.02378   0.01424  -0.1000   0.7805   0.2353
  -6.250  -0.2360   0.02378   0.01429  -0.0941   0.7714   0.2445
  -6.000  -0.2220   0.02340   0.01395  -0.0918   0.7657   0.2596
  -5.750  -0.1994   0.02289   0.01347  -0.0912   0.7617   0.2796
  -5.500  -0.2032   0.02289   0.01353  -0.0856   0.7535   0.2938
  -5.250  -0.1920   0.02260   0.01330  -0.0827   0.7475   0.3144
  -5.000  -0.1700   0.02215   0.01291  -0.0818   0.7434   0.3417
  -4.750  -0.1667   0.02207   0.01290  -0.0774   0.7365   0.3632
  -4.500  -0.1599   0.02193   0.01285  -0.0737   0.7299   0.3871
  -4.250  -0.1384   0.02159   0.01260  -0.0725   0.7256   0.4174
  -4.000  -0.1110   0.02126   0.01234  -0.0724   0.7223   0.4497
  -3.750  -0.1203   0.02149   0.01268  -0.0655   0.7134   0.4685
  -3.500  -0.1009   0.02137   0.01262  -0.0638   0.7086   0.4968
  -3.250  -0.0709   0.02117   0.01242  -0.0640   0.7051   0.5251
  -3.000  -0.0660   0.02133   0.01263  -0.0597   0.6984   0.5449
  -2.750  -0.0553   0.02143   0.01275  -0.0564   0.6921   0.5648
  -2.500  -0.0279   0.02136   0.01265  -0.0561   0.6881   0.5859
  -2.250   0.0077   0.02123   0.01247  -0.0573   0.6850   0.6061
  -2.000  -0.0032   0.02158   0.01285  -0.0502   0.6766   0.6202
  -1.750   0.0174   0.02165   0.01291  -0.0486   0.6716   0.6362
  -1.500   0.0508   0.02159   0.01281  -0.0493   0.6681   0.6531
  -1.250   0.0741   0.02165   0.01283  -0.0483   0.6637   0.6683
  -1.000   0.0623   0.02194   0.01314  -0.0410   0.6556   0.6815
  -0.750   0.0916   0.02197   0.01317  -0.0410   0.6514   0.6950
  -0.500   0.1300   0.02189   0.01301  -0.0426   0.6483   0.7085
  -0.250   0.1240   0.02217   0.01330  -0.0365   0.6414   0.7207
   0.000   0.1372   0.02236   0.01352  -0.0337   0.6353   0.7312
   0.250   0.1657   0.02224   0.01331  -0.0337   0.6315   0.7438
   0.500   0.2113   0.02213   0.01314  -0.0367   0.6287   0.7530
   0.750   0.1888   0.02268   0.01375  -0.0279   0.6201   0.7648
   1.000   0.2139   0.02277   0.01384  -0.0273   0.6152   0.7739
   1.250   0.2465   0.02256   0.01354  -0.0281   0.6118   0.7850
   1.500   0.2806   0.02257   0.01353  -0.0291   0.6080   0.7933
   1.750   0.2639   0.02323   0.01427  -0.0217   0.5995   0.8059
   2.000   0.2974   0.02322   0.01424  -0.0227   0.5954   0.8147
   2.500   0.3416   0.02356   0.01456  -0.0210   0.5855   0.8356
   2.750   0.3544   0.02390   0.01492  -0.0188   0.5794   0.8474
   3.000   0.3960   0.02381   0.01479  -0.0213   0.5758   0.8557
   3.250   0.4390   0.02354   0.01444  -0.0239   0.5729   0.8654
   3.500   0.4394   0.02457   0.01561  -0.0203   0.5645   0.8769
   3.750   0.4696   0.02476   0.01579  -0.0211   0.5596   0.8872
   4.000   0.5184   0.02463   0.01561  -0.0249   0.5562   0.8937
   4.250   0.5504   0.02482   0.01578  -0.0261   0.5517   0.9041
   4.500   0.5651   0.02582   0.01688  -0.0254   0.5440   0.9152
   4.750   0.6054   0.02587   0.01690  -0.0280   0.5398   0.9239
   5.000   0.6569   0.02569   0.01665  -0.0323   0.5367   0.9296
   5.250   0.6710   0.02673   0.01778  -0.0317   0.5294   0.9425
   5.500   0.6997   0.02719   0.01826  -0.0329   0.5237   0.9540
   5.750   0.7473   0.02711   0.01813  -0.0367   0.5200   0.9595
   6.000   0.7915   0.02702   0.01798  -0.0399   0.5166   0.9679
   6.250   0.7987   0.02854   0.01965  -0.0391   0.5084   0.9833
   6.500   0.8394   0.02868   0.01977  -0.0422   0.5038   0.9917
   6.750   0.8904   0.02846   0.01949  -0.0465   0.5004   0.9980
   7.000   0.8571   0.02969   0.02075  -0.0382   0.4940   1.0000
   7.250   0.8413   0.03067   0.02172  -0.0324   0.4879   1.0000
   7.500   0.8628   0.03059   0.02158  -0.0315   0.4842   1.0000
   7.750   0.8978   0.03016   0.02107  -0.0323   0.4814   1.0000
   8.000   0.8415   0.03323   0.02425  -0.0224   0.4718   1.0000
   8.250   0.8587   0.03352   0.02451  -0.0211   0.4677   1.0000
   8.500   0.8907   0.03315   0.02409  -0.0215   0.4649   1.0000
   8.750   0.8564   0.03607   0.02709  -0.0152   0.4564   1.0000
   9.000   0.8600   0.03719   0.02822  -0.0129   0.4508   1.0000
   9.250   0.8901   0.03686   0.02786  -0.0129   0.4480   1.0000
   9.500   0.9278   0.03617   0.02714  -0.0138   0.4459   1.0000
  10.000   0.8887   0.04148   0.03257  -0.0058   0.4307   1.0000
  10.250   0.9257   0.04066   0.03172  -0.0064   0.4288   1.0000
  10.750   0.8845   0.04716   0.03836   0.0001   0.4128   1.0000
  11.000   0.9226   0.04603   0.03721  -0.0004   0.4111   1.0000
  11.250   0.9623   0.04492   0.03610  -0.0010   0.4097   1.0000
  11.750   0.8244   0.06139   0.05281   0.0075   0.3796   1.0000
  12.000   0.8513   0.06093   0.05237   0.0078   0.3777   1.0000
  12.250   0.8812   0.06020   0.05165   0.0080   0.3763   1.0000
  12.500   0.9154   0.05909   0.05055   0.0081   0.3752   1.0000
  15.000   0.8688   0.09000   0.08201   0.0135   0.3045   1.0000
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