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E374 (e374-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: E374 (e374-il)
Reynolds number: 50,000
Max Cl/Cd: 34.04 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e374-il-50000-n5.txt
Download as CSV file: xf-e374-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E374                                            
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4534   0.10064   0.09370  -0.0366   1.0000   0.0393
  -9.750  -0.4537   0.09629   0.08942  -0.0383   1.0000   0.0392
  -9.500  -0.4565   0.09148   0.08468  -0.0408   1.0000   0.0391
  -9.250  -0.4575   0.08723   0.08050  -0.0425   1.0000   0.0387
  -9.000  -0.4632   0.08208   0.07541  -0.0458   1.0000   0.0386
  -8.750  -0.4713   0.07760   0.07100  -0.0478   1.0000   0.0382
  -8.500  -0.4833   0.07375   0.06718  -0.0483   1.0000   0.0380
  -8.250  -0.4965   0.06994   0.06338  -0.0481   1.0000   0.0379
  -8.000  -0.5065   0.06633   0.05974  -0.0474   1.0000   0.0376
  -7.750  -0.5174   0.06263   0.05593  -0.0461   1.0000   0.0378
  -7.500  -0.5248   0.05922   0.05240  -0.0443   1.0000   0.0379
  -7.250  -0.5315   0.05582   0.04878  -0.0420   1.0000   0.0382
  -7.000  -0.5359   0.05264   0.04534  -0.0394   1.0000   0.0385
  -6.750  -0.5388   0.04965   0.04202  -0.0365   1.0000   0.0390
  -6.500  -0.5397   0.04690   0.03890  -0.0333   1.0000   0.0394
  -6.250  -0.5388   0.04413   0.03591  -0.0303   1.0000   0.0400
  -6.000  -0.5352   0.04166   0.03313  -0.0275   1.0000   0.0406
  -5.750  -0.5291   0.03942   0.03062  -0.0249   1.0000   0.0413
  -5.500  -0.5138   0.03705   0.02790  -0.0237   0.9974   0.0426
  -5.250  -0.4814   0.03440   0.02479  -0.0254   0.9888   0.0456
  -5.000  -0.4468   0.03213   0.02184  -0.0267   0.9805   0.0521
  -4.750  -0.4136   0.03005   0.01965  -0.0282   0.9724   0.0581
  -4.500  -0.3801   0.02838   0.01775  -0.0294   0.9641   0.0685
  -4.250  -0.3436   0.02682   0.01598  -0.0310   0.9572   0.0821
  -4.000  -0.3113   0.02560   0.01463  -0.0320   0.9481   0.1054
  -3.750  -0.2765   0.02423   0.01342  -0.0338   0.9409   0.1485
  -3.500  -0.2470   0.02283   0.01249  -0.0350   0.9321   0.2338
  -3.250  -0.2236   0.02141   0.01192  -0.0349   0.9231   0.3930
  -3.000  -0.1966   0.02023   0.01197  -0.0332   0.9170   0.6581
  -2.750  -0.1316   0.02053   0.01232  -0.0369   0.9162   0.8610
  -2.500  -0.0482   0.02096   0.01220  -0.0459   0.9167   0.9354
  -2.250   0.0354   0.02089   0.01159  -0.0566   0.9165   0.9774
  -2.000   0.1045   0.02055   0.01086  -0.0655   0.9133   1.0000
  -1.750   0.1354   0.02045   0.01050  -0.0670   0.9022   1.0000
  -1.500   0.1631   0.02041   0.01026  -0.0677   0.8908   1.0000
  -1.250   0.1905   0.02040   0.01006  -0.0683   0.8801   1.0000
  -1.000   0.2197   0.02038   0.00987  -0.0691   0.8709   1.0000
  -0.750   0.2438   0.02045   0.00978  -0.0690   0.8603   1.0000
  -0.500   0.2658   0.02057   0.00979  -0.0684   0.8498   1.0000
  -0.250   0.2901   0.02067   0.00977  -0.0681   0.8407   1.0000
   0.000   0.3137   0.02080   0.00980  -0.0677   0.8316   1.0000
   0.250   0.3328   0.02104   0.00996  -0.0665   0.8215   1.0000
   0.500   0.3563   0.02121   0.01005  -0.0659   0.8133   1.0000
   0.750   0.3774   0.02145   0.01025  -0.0650   0.8043   1.0000
   1.000   0.3970   0.02175   0.01051  -0.0639   0.7951   1.0000
   1.250   0.4225   0.02192   0.01065  -0.0635   0.7880   1.0000
   1.500   0.4392   0.02232   0.01104  -0.0619   0.7782   1.0000
   1.750   0.4618   0.02259   0.01130  -0.0611   0.7706   1.0000
   2.000   0.4820   0.02293   0.01167  -0.0600   0.7620   1.0000
   2.250   0.5007   0.02333   0.01209  -0.0586   0.7532   1.0000
   2.500   0.5252   0.02357   0.01236  -0.0580   0.7461   1.0000
   2.750   0.5413   0.02407   0.01291  -0.0562   0.7364   1.0000
   3.000   0.5652   0.02434   0.01325  -0.0555   0.7291   1.0000
   3.250   0.5837   0.02478   0.01376  -0.0540   0.7197   1.0000
   3.500   0.6018   0.02523   0.01429  -0.0525   0.7102   1.0000
   3.750   0.6290   0.02536   0.01451  -0.0520   0.7028   1.0000
   4.000   0.6445   0.02589   0.01513  -0.0500   0.6917   1.0000
   4.250   0.6631   0.02630   0.01570  -0.0484   0.6811   1.0000
   4.500   0.6864   0.02650   0.01602  -0.0472   0.6714   1.0000
   4.750   0.7111   0.02660   0.01626  -0.0462   0.6610   1.0000
   5.000   0.7296   0.02692   0.01673  -0.0443   0.6484   1.0000
   5.250   0.7495   0.02714   0.01716  -0.0426   0.6354   1.0000
   5.500   0.7705   0.02726   0.01745  -0.0409   0.6216   1.0000
   5.750   0.7924   0.02727   0.01764  -0.0392   0.6070   1.0000
   6.000   0.8158   0.02711   0.01767  -0.0375   0.5912   1.0000
   6.250   0.8336   0.02716   0.01791  -0.0352   0.5725   1.0000
   6.500   0.8526   0.02704   0.01799  -0.0328   0.5518   1.0000
   6.750   0.8699   0.02694   0.01815  -0.0302   0.5283   1.0000
   7.000   0.8860   0.02682   0.01821  -0.0274   0.5006   1.0000
   7.250   0.9009   0.02671   0.01822  -0.0244   0.4661   1.0000
   7.500   0.9122   0.02680   0.01832  -0.0209   0.4217   1.0000
   7.750   0.9198   0.02720   0.01855  -0.0172   0.3633   1.0000
   8.000   0.9222   0.02816   0.01911  -0.0132   0.3002   1.0000
   8.250   0.9186   0.02970   0.02024  -0.0091   0.2457   1.0000
   8.500   0.9114   0.03153   0.02172  -0.0051   0.2015   1.0000
   8.750   0.9054   0.03358   0.02348  -0.0018   0.1630   1.0000
   9.000   0.9006   0.03583   0.02545   0.0008   0.1333   1.0000
   9.250   0.8991   0.03808   0.02756   0.0029   0.1096   1.0000
   9.500   0.8987   0.04038   0.02980   0.0048   0.0940   1.0000
   9.750   0.9013   0.04264   0.03202   0.0065   0.0815   1.0000
  10.000   0.9093   0.04465   0.03412   0.0082   0.0721   1.0000
  10.250   0.9185   0.04663   0.03618   0.0096   0.0643   1.0000
  10.500   0.9277   0.04862   0.03820   0.0108   0.0578   1.0000
  10.750   0.9519   0.05036   0.04021   0.0123   0.0527   1.0000
  11.000   0.9762   0.05252   0.04264   0.0136   0.0487   1.0000
  11.250   0.9933   0.05501   0.04513   0.0143   0.0452   1.0000
  11.500   0.9980   0.05803   0.04858   0.0155   0.0427   1.0000
  11.750   0.9988   0.06127   0.05219   0.0164   0.0407   1.0000
  12.000   0.9970   0.06486   0.05616   0.0171   0.0394   1.0000
  12.250   0.9914   0.06876   0.06036   0.0174   0.0388   1.0000
  12.500   0.9814   0.07308   0.06495   0.0173   0.0383   1.0000
  12.750   0.9677   0.07788   0.07001   0.0165   0.0380   1.0000
  13.000   0.9508   0.08321   0.07558   0.0150   0.0379   1.0000
  13.250   0.9302   0.08941   0.08200   0.0125   0.0382   1.0000
  13.500   0.9071   0.09651   0.08924   0.0089   0.0387   1.0000
  13.750   0.8812   0.10492   0.09780   0.0041   0.0393   1.0000
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