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E195 (11.82%) (e195-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: E195 (11.82%) (e195-il)
Reynolds number: 50,000
Max Cl/Cd: 31.82 at α=8.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e195-il-50000-n5.txt
Download as CSV file: xf-e195-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E195  (11.82%)                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3819   0.09959   0.09258  -0.0425   1.0000   0.0536
  -9.500  -0.3821   0.09569   0.08876  -0.0439   1.0000   0.0532
  -9.250  -0.3839   0.09168   0.08483  -0.0453   1.0000   0.0526
  -9.000  -0.3869   0.08770   0.08095  -0.0467   1.0000   0.0518
  -8.750  -0.3927   0.08351   0.07688  -0.0484   1.0000   0.0512
  -8.500  -0.4031   0.07899   0.07248  -0.0502   1.0000   0.0505
  -8.250  -0.4191   0.07438   0.06800  -0.0522   1.0000   0.0497
  -8.000  -0.4377   0.06983   0.06358  -0.0535   1.0000   0.0490
  -7.750  -0.4568   0.06582   0.05960  -0.0534   1.0000   0.0483
  -7.500  -0.4751   0.06235   0.05611  -0.0522   1.0000   0.0478
  -7.250  -0.4920   0.05924   0.05291  -0.0502   1.0000   0.0474
  -7.000  -0.5028   0.05585   0.04933  -0.0489   0.9986   0.0470
  -6.750  -0.4819   0.04985   0.04275  -0.0542   0.9857   0.0468
  -6.500  -0.4577   0.04519   0.03747  -0.0577   0.9740   0.0470
  -6.250  -0.4314   0.04139   0.03312  -0.0601   0.9629   0.0477
  -6.000  -0.4021   0.03818   0.02936  -0.0622   0.9530   0.0488
  -5.750  -0.3698   0.03548   0.02615  -0.0641   0.9440   0.0510
  -5.500  -0.3394   0.03334   0.02343  -0.0652   0.9339   0.0547
  -5.250  -0.3057   0.03145   0.02138  -0.0669   0.9262   0.0589
  -5.000  -0.2733   0.02983   0.01950  -0.0679   0.9173   0.0632
  -4.750  -0.2407   0.02829   0.01770  -0.0687   0.9092   0.0693
  -4.500  -0.2080   0.02702   0.01634  -0.0698   0.9013   0.0826
  -4.250  -0.1795   0.02584   0.01517  -0.0703   0.8919   0.1072
  -4.000  -0.1460   0.02454   0.01415  -0.0722   0.8850   0.1686
  -3.750  -0.1208   0.02353   0.01344  -0.0723   0.8751   0.2413
  -3.500  -0.0926   0.02267   0.01295  -0.0728   0.8674   0.3335
  -3.250  -0.0684   0.02220   0.01275  -0.0720   0.8583   0.4267
  -3.000  -0.0444   0.02189   0.01257  -0.0710   0.8499   0.5098
  -2.750  -0.0189   0.02161   0.01240  -0.0699   0.8423   0.5836
  -2.500   0.0030   0.02145   0.01234  -0.0681   0.8337   0.6486
  -2.250   0.0294   0.02125   0.01219  -0.0667   0.8270   0.7160
  -2.000   0.0550   0.02118   0.01215  -0.0653   0.8190   0.7818
  -1.750   0.0979   0.02107   0.01197  -0.0669   0.8133   0.8548
  -1.500   0.1592   0.02098   0.01163  -0.0727   0.8086   0.9221
  -1.250   0.2225   0.02092   0.01128  -0.0799   0.8022   0.9770
  -1.000   0.2679   0.02083   0.01088  -0.0839   0.7964   1.0000
  -0.750   0.2824   0.02111   0.01098  -0.0824   0.7868   1.0000
  -0.500   0.3066   0.02123   0.01087  -0.0820   0.7803   1.0000
  -0.250   0.3230   0.02160   0.01109  -0.0806   0.7711   1.0000
   0.000   0.3477   0.02179   0.01109  -0.0802   0.7650   1.0000
   0.250   0.3657   0.02220   0.01137  -0.0789   0.7564   1.0000
   0.500   0.3922   0.02239   0.01141  -0.0787   0.7508   1.0000
   0.750   0.4095   0.02288   0.01182  -0.0774   0.7422   1.0000
   1.000   0.4372   0.02307   0.01188  -0.0773   0.7369   1.0000
   1.250   0.4540   0.02364   0.01240  -0.0759   0.7282   1.0000
   1.500   0.4812   0.02387   0.01255  -0.0758   0.7229   1.0000
   1.750   0.4988   0.02447   0.01312  -0.0745   0.7146   1.0000
   2.000   0.5251   0.02476   0.01336  -0.0743   0.7090   1.0000
   2.250   0.5440   0.02535   0.01394  -0.0732   0.7013   1.0000
   2.500   0.5688   0.02572   0.01430  -0.0728   0.6951   1.0000
   2.750   0.5896   0.02628   0.01486  -0.0719   0.6881   1.0000
   3.000   0.6121   0.02675   0.01535  -0.0712   0.6812   1.0000
   3.250   0.6359   0.02721   0.01583  -0.0707   0.6750   1.0000
   3.500   0.6551   0.02786   0.01654  -0.0697   0.6672   1.0000
   3.750   0.6826   0.02815   0.01686  -0.0695   0.6618   1.0000
   4.000   0.6979   0.02899   0.01778  -0.0681   0.6528   1.0000
   4.250   0.7275   0.02917   0.01801  -0.0680   0.6477   1.0000
   4.500   0.7409   0.03011   0.01909  -0.0664   0.6378   1.0000
   4.750   0.7658   0.03050   0.01955  -0.0659   0.6311   1.0000
   5.000   0.7847   0.03115   0.02031  -0.0647   0.6222   1.0000
   5.250   0.8032   0.03181   0.02109  -0.0635   0.6132   1.0000
   5.500   0.8309   0.03196   0.02139  -0.0631   0.6059   1.0000
   5.750   0.8452   0.03279   0.02236  -0.0614   0.5950   1.0000
   6.000   0.8710   0.03295   0.02266  -0.0607   0.5866   1.0000
   6.250   0.8947   0.03314   0.02300  -0.0597   0.5767   1.0000
   6.500   0.9103   0.03376   0.02378  -0.0579   0.5647   1.0000
   6.750   0.9298   0.03408   0.02431  -0.0565   0.5530   1.0000
   7.000   0.9536   0.03405   0.02446  -0.0552   0.5413   1.0000
   7.250   0.9788   0.03382   0.02442  -0.0539   0.5288   1.0000
   7.500   0.9991   0.03377   0.02456  -0.0521   0.5142   1.0000
   7.750   1.0154   0.03388   0.02490  -0.0500   0.4980   1.0000
   8.000   1.0317   0.03390   0.02511  -0.0477   0.4805   1.0000
   8.250   1.0519   0.03352   0.02492  -0.0456   0.4614   1.0000
   8.500   1.0612   0.03385   0.02541  -0.0427   0.4397   1.0000
   8.750   1.0746   0.03377   0.02543  -0.0399   0.4157   1.0000
   9.000   1.0816   0.03421   0.02597  -0.0369   0.3883   1.0000
   9.250   1.0865   0.03494   0.02676  -0.0339   0.3567   1.0000
   9.500   1.0906   0.03588   0.02762  -0.0311   0.3212   1.0000
   9.750   1.0920   0.03723   0.02878  -0.0285   0.2848   1.0000
  10.000   1.0895   0.03918   0.03052  -0.0262   0.2510   1.0000
  10.250   1.0855   0.04152   0.03268  -0.0243   0.2216   1.0000
  10.500   1.0809   0.04415   0.03516  -0.0228   0.1954   1.0000
  10.750   1.0762   0.04694   0.03781  -0.0215   0.1729   1.0000
  11.000   1.0713   0.04994   0.04071  -0.0206   0.1515   1.0000
  11.250   1.0664   0.05304   0.04368  -0.0198   0.1333   1.0000
  11.500   1.0615   0.05633   0.04691  -0.0194   0.1144   1.0000
  11.750   1.0562   0.05975   0.05025  -0.0192   0.0984   1.0000
  12.000   1.0517   0.06320   0.05369  -0.0192   0.0849   1.0000
  12.250   1.0488   0.06662   0.05710  -0.0192   0.0735   1.0000
  12.500   1.0465   0.07008   0.06059  -0.0191   0.0638   1.0000
  12.750   1.0454   0.07338   0.06382  -0.0191   0.0582   1.0000
  13.000   1.0482   0.07647   0.06712  -0.0188   0.0519   1.0000
  13.250   1.0483   0.07974   0.07035  -0.0190   0.0480   1.0000
  13.500   1.0537   0.08280   0.07370  -0.0186   0.0440   1.0000
  13.750   1.0590   0.08584   0.07694  -0.0183   0.0418   1.0000
  14.000   1.0629   0.08906   0.08030  -0.0184   0.0399   1.0000
  14.250   1.0678   0.09213   0.08344  -0.0183   0.0383   1.0000
  14.500   1.0672   0.09644   0.08801  -0.0191   0.0373   1.0000
  14.750   1.0609   0.10174   0.09363  -0.0207   0.0366   1.0000
  15.000   1.0506   0.10777   0.09996  -0.0232   0.0361   1.0000
  15.250   1.0367   0.11478   0.10724  -0.0266   0.0357   1.0000
  15.500   1.0214   0.12248   0.11517  -0.0307   0.0357   1.0000
  15.750   1.0056   0.13075   0.12364  -0.0353   0.0361   1.0000
  16.000   0.9871   0.14038   0.13343  -0.0410   0.0364   1.0000
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