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FX 84-W-127 (fx84w127-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: FX 84-W-127 (fx84w127-il)
Reynolds number: 50,000
Max Cl/Cd: 24.33 at α=10°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx84w127-il-50000-n5.txt
Download as CSV file: xf-fx84w127-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 84-W-127                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3351   0.11037   0.10342  -0.0526   1.0000   0.0651
 -10.250  -0.3352   0.10695   0.10007  -0.0534   1.0000   0.0650
 -10.000  -0.3367   0.10378   0.09699  -0.0536   1.0000   0.0649
  -9.750  -0.3400   0.10107   0.09437  -0.0531   1.0000   0.0646
  -9.500  -0.3478   0.09875   0.09216  -0.0518   1.0000   0.0642
  -9.250  -0.3598   0.09677   0.09030  -0.0499   1.0000   0.0638
  -9.000  -0.3745   0.09507   0.08871  -0.0476   1.0000   0.0634
  -8.750  -0.3915   0.09340   0.08715  -0.0453   1.0000   0.0629
  -8.500  -0.3929   0.08916   0.08295  -0.0486   0.9934   0.0623
  -8.250  -0.3899   0.08335   0.07713  -0.0554   0.9832   0.0616
  -8.000  -0.3891   0.07697   0.07070  -0.0630   0.9719   0.0609
  -7.750  -0.3886   0.07070   0.06430  -0.0692   0.9607   0.0607
  -7.500  -0.3881   0.06510   0.05848  -0.0737   0.9502   0.0609
  -7.250  -0.3836   0.05956   0.05260  -0.0779   0.9413   0.0619
  -7.000  -0.3785   0.05458   0.04715  -0.0803   0.9319   0.0632
  -6.750  -0.3699   0.05025   0.04225  -0.0814   0.9231   0.0643
  -6.500  -0.3524   0.04615   0.03754  -0.0829   0.9163   0.0654
  -6.250  -0.3326   0.04410   0.03535  -0.0832   0.9093   0.0676
  -6.000  -0.3096   0.04222   0.03322  -0.0838   0.9027   0.0714
  -5.750  -0.2854   0.03960   0.03000  -0.0845   0.8969   0.0752
  -5.500  -0.2656   0.03741   0.02723  -0.0839   0.8892   0.0781
  -5.250  -0.2354   0.03603   0.02580  -0.0851   0.8845   0.0835
  -5.000  -0.2154   0.03476   0.02418  -0.0841   0.8768   0.0887
  -4.750  -0.1869   0.03337   0.02254  -0.0844   0.8714   0.0944
  -4.500  -0.1586   0.03238   0.02134  -0.0847   0.8659   0.1030
  -4.250  -0.1361   0.03152   0.02039  -0.0839   0.8587   0.1100
  -4.000  -0.1044   0.03064   0.01935  -0.0845   0.8542   0.1224
  -3.750  -0.0829   0.03009   0.01870  -0.0835   0.8470   0.1339
  -3.500  -0.0556   0.02947   0.01802  -0.0835   0.8411   0.1510
  -3.250  -0.0230   0.02869   0.01731  -0.0845   0.8372   0.1749
  -3.000  -0.0077   0.02838   0.01702  -0.0827   0.8284   0.1994
  -2.750   0.0200   0.02765   0.01650  -0.0829   0.8235   0.2463
  -2.500   0.0375   0.02707   0.01631  -0.0817   0.8162   0.3150
  -2.250   0.0554   0.02616   0.01623  -0.0801   0.8101   0.4673
  -2.000   0.0748   0.02559   0.01650  -0.0763   0.8061   0.6915
  -1.750   0.0867   0.02589   0.01693  -0.0722   0.7975   0.8046
  -1.500   0.1307   0.02600   0.01690  -0.0733   0.7936   0.9021
  -1.250   0.2283   0.02591   0.01639  -0.0854   0.7925   0.9755
  -1.000   0.2852   0.02588   0.01606  -0.0915   0.7881   1.0000
  -0.750   0.2921   0.02621   0.01624  -0.0887   0.7792   1.0000
  -0.500   0.3105   0.02634   0.01619  -0.0874   0.7732   1.0000
  -0.250   0.3163   0.02679   0.01651  -0.0843   0.7641   1.0000
   0.000   0.3425   0.02683   0.01636  -0.0841   0.7597   1.0000
   0.250   0.3453   0.02747   0.01688  -0.0807   0.7495   1.0000
   0.500   0.3723   0.02757   0.01682  -0.0805   0.7450   1.0000
   0.750   0.3798   0.02823   0.01738  -0.0779   0.7355   1.0000
   1.000   0.4069   0.02838   0.01740  -0.0778   0.7306   1.0000
   1.250   0.4188   0.02903   0.01796  -0.0758   0.7219   1.0000
   1.500   0.4444   0.02926   0.01809  -0.0755   0.7163   1.0000
   2.000   0.4836   0.03021   0.01891  -0.0736   0.7021   1.0000
   2.250   0.5158   0.03024   0.01886  -0.0740   0.6984   1.0000
   2.500   0.5236   0.03123   0.01982  -0.0718   0.6880   1.0000
   2.750   0.5550   0.03129   0.01984  -0.0721   0.6839   1.0000
   3.000   0.5641   0.03231   0.02085  -0.0702   0.6740   1.0000
   3.250   0.5939   0.03245   0.02097  -0.0704   0.6694   1.0000
   3.500   0.6047   0.03346   0.02199  -0.0687   0.6600   1.0000
   3.750   0.6329   0.03367   0.02221  -0.0686   0.6549   1.0000
   4.000   0.6455   0.03464   0.02320  -0.0672   0.6459   1.0000
   4.250   0.6718   0.03495   0.02353  -0.0669   0.6402   1.0000
   4.750   0.7103   0.03624   0.02491  -0.0652   0.6253   1.0000
   5.250   0.7480   0.03756   0.02633  -0.0633   0.6100   1.0000
   5.750   0.7856   0.03892   0.02786  -0.0614   0.5946   1.0000
   6.250   0.8238   0.04026   0.02937  -0.0596   0.5789   1.0000
   6.750   0.8633   0.04147   0.03082  -0.0579   0.5631   1.0000
   7.000   0.8680   0.04315   0.03259  -0.0562   0.5512   1.0000
   7.250   0.9062   0.04232   0.03192  -0.0562   0.5471   1.0000
   7.500   0.9095   0.04405   0.03377  -0.0544   0.5344   1.0000
   8.000   0.9544   0.04454   0.03457  -0.0526   0.5177   1.0000
   8.250   0.9595   0.04618   0.03634  -0.0510   0.5050   1.0000
   8.750   1.0092   0.04596   0.03651  -0.0490   0.4873   1.0000
   9.000   1.0172   0.04720   0.03790  -0.0475   0.4741   1.0000
   9.250   1.0315   0.04773   0.03861  -0.0459   0.4608   1.0000
   9.500   1.0526   0.04731   0.03839  -0.0443   0.4466   1.0000
   9.750   1.0794   0.04588   0.03713  -0.0423   0.4294   1.0000
  10.000   1.0984   0.04514   0.03651  -0.0402   0.4084   1.0000
  10.250   1.1030   0.04614   0.03762  -0.0382   0.3855   1.0000
  10.500   1.1117   0.04680   0.03837  -0.0364   0.3607   1.0000
  10.750   1.1196   0.04763   0.03923  -0.0346   0.3323   1.0000
  11.000   1.1233   0.04906   0.04064  -0.0331   0.3008   1.0000
  11.250   1.1258   0.05064   0.04206  -0.0314   0.2649   1.0000
  11.500   1.1232   0.05303   0.04425  -0.0301   0.2288   1.0000
  11.750   1.1172   0.05600   0.04697  -0.0291   0.1962   1.0000
  12.000   1.1100   0.05937   0.05012  -0.0283   0.1693   1.0000
  12.250   1.1028   0.06293   0.05346  -0.0279   0.1484   1.0000
  12.500   1.0979   0.06647   0.05690  -0.0276   0.1314   1.0000
  12.750   1.0947   0.06990   0.06022  -0.0274   0.1185   1.0000
  13.000   1.0932   0.07319   0.06344  -0.0273   0.1079   1.0000
  13.250   1.0951   0.07620   0.06649  -0.0271   0.0983   1.0000
  13.500   1.0984   0.07902   0.06931  -0.0268   0.0912   1.0000
  13.750   1.1026   0.08180   0.07212  -0.0267   0.0844   1.0000
  14.000   1.1096   0.08428   0.07469  -0.0263   0.0788   1.0000
  14.250   1.1171   0.08678   0.07732  -0.0260   0.0737   1.0000
  14.500   1.1267   0.08889   0.07939  -0.0255   0.0694   1.0000
  14.750   1.1331   0.09191   0.08276  -0.0256   0.0656   1.0000
  15.000   1.1410   0.09465   0.08568  -0.0255   0.0625   1.0000
  15.250   1.1539   0.09649   0.08750  -0.0250   0.0593   1.0000
  15.500   1.1536   0.10064   0.09195  -0.0258   0.0572   1.0000
  15.750   1.1482   0.10564   0.09728  -0.0274   0.0556   1.0000
  16.000   1.1410   0.11105   0.10297  -0.0294   0.0543   1.0000
  16.250   1.1314   0.11703   0.10922  -0.0319   0.0534   1.0000
  16.500   1.1178   0.12397   0.11641  -0.0353   0.0529   1.0000
  16.750   1.0988   0.13240   0.12509  -0.0400   0.0527   1.0000
  17.000   1.0702   0.14384   0.13677  -0.0470   0.0531   1.0000
  17.250   1.0313   0.15982   0.15291  -0.0571   0.0542   1.0000
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