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EPPLER 343 AIRFOIL (e343-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 343 AIRFOIL (e343-il)
Reynolds number: 500,000
Max Cl/Cd: 92.64 at α=11°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e343-il-500000.txt
Download as CSV file: xf-e343-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 343 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3103   0.10743   0.10525  -0.0267   1.0000   0.0150
 -10.250  -0.3076   0.10417   0.10202  -0.0277   1.0000   0.0152
 -10.000  -0.3057   0.10076   0.09863  -0.0289   1.0000   0.0152
  -9.750  -0.1766   0.07982   0.07726  -0.0525   0.7981   0.0174
  -9.500  -0.1814   0.07536   0.07268  -0.0543   0.7706   0.0175
  -9.250  -0.1891   0.07011   0.06735  -0.0570   0.7512   0.0175
  -9.000  -0.1951   0.06529   0.06247  -0.0597   0.7341   0.0175
  -8.750  -0.2097   0.05936   0.05647  -0.0643   0.7215   0.0175
  -8.500  -0.2547   0.06720   0.06429  -0.0688   0.7585   0.0172
  -8.250  -0.2684   0.06404   0.06097  -0.0676   0.7336   0.0172
  -8.000  -0.2887   0.06023   0.05696  -0.0648   0.7161   0.0174
  -7.750  -0.2942   0.05711   0.05365  -0.0627   0.6986   0.0175
  -7.500  -0.3019   0.05321   0.04948  -0.0598   0.6847   0.0175
  -7.000  -0.2742   0.03620   0.03252  -0.0542   0.6338   0.0180
  -6.750  -0.2698   0.03375   0.02995  -0.0524   0.6231   0.0182
  -6.500  -0.2641   0.03123   0.02729  -0.0506   0.6126   0.0185
  -6.250  -0.2570   0.02862   0.02454  -0.0486   0.6031   0.0190
  -6.000  -0.2488   0.02594   0.02166  -0.0465   0.5937   0.0196
  -5.750  -0.2505   0.03718   0.03239  -0.0460   0.5987   0.0201
  -5.250  -0.2275   0.03145   0.02604  -0.0403   0.5806   0.0220
  -5.000  -0.2105   0.03007   0.02451  -0.0389   0.5709   0.0226
  -4.750  -0.1923   0.02849   0.02274  -0.0371   0.5612   0.0236
  -4.500  -0.1769   0.02599   0.01974  -0.0341   0.5536   0.0263
  -4.250  -0.1568   0.01924   0.01209  -0.0298   0.5476   0.0148
  -4.000  -0.1308   0.01773   0.01033  -0.0289   0.5391   0.0137
  -3.750  -0.1037   0.01626   0.00864  -0.0283   0.5310   0.0135
  -3.500  -0.0771   0.01534   0.00751  -0.0277   0.5229   0.0138
  -3.250  -0.0510   0.01468   0.00672  -0.0271   0.5154   0.0140
  -3.000  -0.0267   0.01390   0.00586  -0.0262   0.5076   0.0149
  -2.750  -0.0028   0.01347   0.00539  -0.0254   0.5006   0.0155
  -2.500   0.0214   0.01309   0.00498  -0.0245   0.4936   0.0165
  -2.250   0.0449   0.01280   0.00459  -0.0235   0.4871   0.0179
  -2.000   0.0686   0.01249   0.00430  -0.0226   0.4813   0.0197
  -1.750   0.0922   0.01218   0.00395  -0.0216   0.4753   0.0219
  -1.500   0.1158   0.01195   0.00367  -0.0206   0.4698   0.0258
  -1.250   0.1390   0.01163   0.00338  -0.0196   0.4646   0.0377
  -1.000   0.1596   0.01111   0.00320  -0.0182   0.4593   0.1182
  -0.750   0.1553   0.00925   0.00291  -0.0126   0.4555   0.5676
  -0.500   0.1568   0.00890   0.00358  -0.0059   0.4515   0.8714
  -0.250   0.1758   0.00929   0.00394  -0.0031   0.4474   0.9013
   0.000   0.2072   0.00989   0.00452  -0.0024   0.4427   0.9216
   0.250   0.3020   0.01123   0.00563  -0.0147   0.4355   0.9331
   0.500   0.3920   0.01197   0.00623  -0.0268   0.4289   0.9418
   0.750   0.4350   0.01212   0.00630  -0.0298   0.4244   0.9459
   1.000   0.4606   0.01217   0.00627  -0.0294   0.4206   0.9489
   1.250   0.4927   0.01225   0.00624  -0.0305   0.4165   0.9502
   1.500   0.5226   0.01224   0.00622  -0.0310   0.4135   0.9522
   1.750   0.5430   0.01227   0.00623  -0.0296   0.4099   0.9555
   2.000   0.5753   0.01227   0.00618  -0.0307   0.4063   0.9566
   2.250   0.6052   0.01231   0.00616  -0.0313   0.4029   0.9580
   2.500   0.6315   0.01242   0.00621  -0.0312   0.3995   0.9600
   2.750   0.6520   0.01243   0.00623  -0.0298   0.3969   0.9626
   3.000   0.6836   0.01242   0.00621  -0.0308   0.3935   0.9636
   3.250   0.7128   0.01243   0.00621  -0.0313   0.3904   0.9648
   3.500   0.7391   0.01248   0.00623  -0.0312   0.3876   0.9662
   3.750   0.7609   0.01262   0.00631  -0.0301   0.3844   0.9684
   4.000   0.7847   0.01267   0.00636  -0.0295   0.3817   0.9698
   4.250   0.8139   0.01266   0.00639  -0.0300   0.3789   0.9706
   4.500   0.8431   0.01269   0.00643  -0.0306   0.3760   0.9716
   4.750   0.8699   0.01273   0.00646  -0.0306   0.3729   0.9728
   5.000   0.8940   0.01281   0.00652  -0.0302   0.3701   0.9738
   5.250   0.9172   0.01301   0.00668  -0.0295   0.3670   0.9751
   5.500   0.9356   0.01307   0.00679  -0.0278   0.3648   0.9770
   5.750   0.9632   0.01308   0.00685  -0.0280   0.3620   0.9776
   6.000   0.9899   0.01312   0.00691  -0.0281   0.3589   0.9782
   6.250   1.0169   0.01318   0.00699  -0.0283   0.3558   0.9790
   6.500   1.0441   0.01331   0.00710  -0.0285   0.3526   0.9800
   6.750   1.0689   0.01347   0.00727  -0.0283   0.3496   0.9808
   7.000   1.0922   0.01351   0.00739  -0.0277   0.3467   0.9817
   7.250   1.1147   0.01358   0.00751  -0.0269   0.3435   0.9826
   7.500   1.1362   0.01367   0.00763  -0.0260   0.3404   0.9837
   7.750   1.1558   0.01382   0.00778  -0.0247   0.3372   0.9852
   8.000   1.1797   0.01400   0.00798  -0.0243   0.3336   0.9859
   8.250   1.2054   0.01404   0.00812  -0.0243   0.3302   0.9866
   8.500   1.2306   0.01412   0.00826  -0.0242   0.3265   0.9872
   8.750   1.2550   0.01423   0.00839  -0.0240   0.3226   0.9880
   9.000   1.2785   0.01447   0.00862  -0.0237   0.3185   0.9889
   9.250   1.3019   0.01454   0.00881  -0.0233   0.3148   0.9898
   9.500   1.3256   0.01464   0.00898  -0.0229   0.3101   0.9911
   9.750   1.3481   0.01482   0.00918  -0.0224   0.3058   0.9924
  10.000   1.3681   0.01501   0.00943  -0.0214   0.3011   0.9935
  10.250   1.3901   0.01515   0.00966  -0.0208   0.2963   0.9946
  10.500   1.4139   0.01534   0.00988  -0.0207   0.2907   0.9955
  10.750   1.4371   0.01556   0.01017  -0.0205   0.2851   0.9966
  11.000   1.4600   0.01576   0.01045  -0.0202   0.2786   0.9978
  11.250   1.4807   0.01609   0.01079  -0.0197   0.2724   0.9991
  11.500   1.5003   0.01632   0.01113  -0.0188   0.2650   1.0000
  11.750   1.4986   0.01664   0.01144  -0.0138   0.2596   1.0000
  12.000   1.4922   0.01681   0.01169  -0.0078   0.2547   1.0000
  12.250   1.4800   0.01702   0.01196  -0.0009   0.2496   1.0000
  12.500   1.4621   0.01735   0.01228   0.0067   0.2451   1.0000
  12.750   1.4602   0.01773   0.01273   0.0112   0.2391   1.0000
  13.000   1.4583   0.01845   0.01344   0.0150   0.2315   1.0000
  13.250   1.4629   0.01924   0.01428   0.0174   0.2227   1.0000
  13.500   1.4636   0.02041   0.01546   0.0198   0.2140   1.0000
  13.750   1.4645   0.02179   0.01686   0.0217   0.2044   1.0000
  14.000   1.4655   0.02333   0.01844   0.0232   0.1952   1.0000
  14.250   1.4616   0.02539   0.02051   0.0245   0.1867   1.0000
  14.500   1.4577   0.02765   0.02280   0.0255   0.1773   1.0000
  14.750   1.4529   0.03013   0.02532   0.0263   0.1692   1.0000
  15.250   1.4346   0.03626   0.03151   0.0272   0.1534   1.0000
  15.500   1.4199   0.04002   0.03530   0.0274   0.1467   1.0000
  15.750   1.4095   0.04347   0.03880   0.0274   0.1395   1.0000
  16.000   1.3935   0.04759   0.04296   0.0272   0.1340   1.0000
  16.250   1.3832   0.05129   0.04671   0.0268   0.1273   1.0000
  16.500   1.3650   0.05597   0.05141   0.0261   0.1218   1.0000
  16.750   1.3561   0.05972   0.05522   0.0255   0.1158   1.0000
  17.000   1.3408   0.06435   0.05988   0.0246   0.1108   1.0000
  17.250   1.3316   0.06832   0.06390   0.0237   0.1052   1.0000
  17.500   1.3196   0.07271   0.06832   0.0226   0.1003   1.0000
  17.750   1.3099   0.07692   0.07258   0.0214   0.0960   1.0000
  18.000   1.3005   0.08118   0.07687   0.0202   0.0908   1.0000
  18.250   1.2872   0.08600   0.08171   0.0187   0.0864   1.0000
  18.500   1.2840   0.08956   0.08534   0.0175   0.0822   1.0000
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