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EPPLER 379 AIRFOIL (e379-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 379 AIRFOIL (e379-il)
Reynolds number: 100,000
Max Cl/Cd: 74.6 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e379-il-100000.txt
Download as CSV file: xf-e379-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 379 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.0788   0.09222   0.08840  -0.0421   0.9097   0.0123
  -7.000  -0.0648   0.09043   0.08654  -0.0439   0.8871   0.0127
  -6.750  -0.0521   0.08893   0.08498  -0.0454   0.8670   0.0130
  -6.500  -0.0374   0.08770   0.08370  -0.0473   0.8505   0.0133
  -6.250  -0.0202   0.08683   0.08276  -0.0500   0.8358   0.0135
  -6.000   0.0013   0.08631   0.08218  -0.0539   0.8223   0.0138
  -5.750   0.0239   0.08547   0.08126  -0.0578   0.8098   0.0139
  -5.500   0.0504   0.08492   0.08063  -0.0626   0.7981   0.0140
  -5.250   0.0681   0.08145   0.07716  -0.0646   0.7884   0.0144
  -5.000   0.0609   0.07366   0.06940  -0.0593   0.7821   0.0157
  -4.750   0.0773   0.07072   0.06636  -0.0609   0.7724   0.0173
  -4.500   0.0984   0.06844   0.06404  -0.0635   0.7639   0.0190
  -4.250   0.1219   0.06622   0.06174  -0.0663   0.7563   0.0209
  -4.000   0.1485   0.06413   0.05961  -0.0698   0.7477   0.0223
  -3.750   0.1792   0.06245   0.05782  -0.0736   0.7408   0.0241
  -3.500   0.2238   0.06250   0.05774  -0.0802   0.7321   0.0253
  -3.250   0.2674   0.06255   0.05761  -0.0861   0.7245   0.0256
  -2.750   0.3049   0.05473   0.04978  -0.0884   0.7119   0.0268
  -2.500   0.3255   0.05163   0.04664  -0.0897   0.7054   0.0285
  -2.250   0.3540   0.04956   0.04448  -0.0922   0.6995   0.0305
  -2.000   0.3858   0.04783   0.04266  -0.0951   0.6927   0.0330
  -1.750   0.4209   0.04656   0.04123  -0.0980   0.6872   0.0359
  -1.500   0.4720   0.04805   0.04246  -0.1028   0.6798   0.0377
  -1.250   0.4945   0.04438   0.03873  -0.1039   0.6756   0.0388
  -1.000   0.5169   0.04167   0.03606  -0.1055   0.6688   0.0419
  -0.750   0.5489   0.04031   0.03448  -0.1073   0.6637   0.0465
  -0.250   0.6135   0.03787   0.03180  -0.1110   0.6520   0.0540
   0.000   0.6176   0.01911   0.01334  -0.1054   0.6367   0.0635
   0.250   0.6426   0.01783   0.01205  -0.1071   0.6309   0.0710
   0.500   0.6734   0.01708   0.01114  -0.1084   0.6259   0.0786
   0.750   0.7042   0.01611   0.00985  -0.1090   0.6223   0.0901
   1.000   0.7333   0.01622   0.00991  -0.1107   0.6152   0.1020
   1.250   0.7615   0.01526   0.00881  -0.1113   0.6112   0.1165
   1.500   0.7904   0.01529   0.00866  -0.1120   0.6062   0.1392
   1.750   0.8164   0.01492   0.00823  -0.1129   0.6003   0.1654
   2.000   0.8428   0.01365   0.00682  -0.1130   0.5967   0.2096
   2.250   0.8655   0.01345   0.00666  -0.1139   0.5903   0.2870
   2.500   0.8927   0.01282   0.00602  -0.1140   0.5856   0.3314
   2.750   0.9235   0.01238   0.00531  -0.1134   0.5825   0.3257
   3.000   0.9511   0.01434   0.00713  -0.1137   0.5749   0.2134
   3.250   0.9844   0.01435   0.00670  -0.1121   0.5712   0.0699
   3.500   1.0099   0.01436   0.00650  -0.1115   0.5664   0.0532
   3.750   1.0856   0.02924   0.02052  -0.1169   0.5706   0.0470
   4.000   1.1111   0.02955   0.02072  -0.1170   0.5646   0.0531
   4.250   1.1360   0.02961   0.02065  -0.1165   0.5593   0.0653
   4.500   1.1643   0.02917   0.01998  -0.1156   0.5561   0.1082
   4.750   1.1888   0.02961   0.02125  -0.1168   0.5480   1.0000
   5.000   1.2150   0.02975   0.02116  -0.1160   0.5440   1.0000
   5.250   1.2347   0.03103   0.02246  -0.1158   0.5368   1.0000
   5.500   1.2596   0.03128   0.02262  -0.1151   0.5316   1.0000
   5.750   1.2819   0.03198   0.02332  -0.1145   0.5256   1.0000
   6.000   1.3040   0.03262   0.02399  -0.1140   0.5190   1.0000
   6.250   1.3337   0.03206   0.02338  -0.1130   0.5158   1.0000
   6.500   1.3592   0.03099   0.02225  -0.1115   0.5037   1.0000
   6.750   1.3923   0.02648   0.01730  -0.1081   0.4783   1.0000
   7.000   1.4179   0.02437   0.01497  -0.1061   0.4550   1.0000
   7.250   1.4406   0.02285   0.01327  -0.1043   0.4263   1.0000
   7.500   1.4633   0.02300   0.01354  -0.1036   0.4156   1.0000
   7.750   1.4863   0.02317   0.01383  -0.1029   0.4060   1.0000
   8.000   1.5089   0.02340   0.01423  -0.1022   0.3962   1.0000
   8.250   1.5251   0.02337   0.01410  -0.1007   0.3531   1.0000
   8.500   1.5428   0.02393   0.01464  -0.0996   0.3225   1.0000
   8.750   1.5586   0.02477   0.01546  -0.0983   0.2911   1.0000
   9.000   1.5622   0.02689   0.01822  -0.0956   0.2235   1.0000
   9.250   1.5454   0.03053   0.02131  -0.0921   0.1484   1.0000
   9.500   1.5305   0.03364   0.02426  -0.0888   0.1093   1.0000
   9.750   1.5133   0.03731   0.02776  -0.0867   0.0771   1.0000
  10.000   1.4915   0.04207   0.03229  -0.0856   0.0376   1.0000
  10.250   1.4746   0.04678   0.03692  -0.0851   0.0221   1.0000
  10.500   1.4664   0.05081   0.04109  -0.0847   0.0191   1.0000
  10.750   1.4577   0.05500   0.04546  -0.0845   0.0168   1.0000
  11.000   1.4507   0.05905   0.04971  -0.0844   0.0151   1.0000
  11.250   1.4429   0.06331   0.05422  -0.0844   0.0141   1.0000
  11.500   1.4359   0.06754   0.05865  -0.0845   0.0136   1.0000
  11.750   1.4297   0.07176   0.06309  -0.0848   0.0135   1.0000
  12.000   1.4224   0.07622   0.06778  -0.0852   0.0134   1.0000
  12.250   1.4143   0.08104   0.07283  -0.0859   0.0135   1.0000
  12.500   1.4060   0.08600   0.07801  -0.0867   0.0135   1.0000
  12.750   1.3981   0.09104   0.08325  -0.0877   0.0135   1.0000
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