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EPPLER 326 AIRFOIL (e326-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 326 AIRFOIL (e326-il)
Reynolds number: 500,000
Max Cl/Cd: 76.49 at α=9.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e326-il-500000.txt
Download as CSV file: xf-e326-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 326 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.5068   0.08613   0.08397  -0.0208   1.0000   0.0163
  -9.750  -0.5141   0.08127   0.07910  -0.0241   1.0000   0.0162
  -9.000  -0.5657   0.06686   0.06448  -0.0265   1.0000   0.0163
  -8.750  -0.5872   0.06302   0.06048  -0.0228   1.0000   0.0165
  -8.500  -0.6001   0.05992   0.05724  -0.0191   1.0000   0.0165
  -8.250  -0.6111   0.05663   0.05374  -0.0152   1.0000   0.0166
  -8.000  -0.6252   0.05210   0.04902  -0.0112   1.0000   0.0167
  -7.750  -0.6241   0.04922   0.04612  -0.0088   1.0000   0.0169
  -7.500  -0.6214   0.04712   0.04399  -0.0063   1.0000   0.0172
  -7.250  -0.6173   0.04502   0.04180  -0.0034   1.0000   0.0173
  -7.000  -0.6123   0.04315   0.03986  -0.0006   1.0000   0.0177
  -6.750  -0.5922   0.04043   0.03699  -0.0009   0.9879   0.0183
  -6.500  -0.5570   0.03736   0.03320  -0.0017   0.9426   0.0209
  -6.250  -0.5271   0.03168   0.02720  -0.0046   0.8865   0.0218
  -6.000  -0.5102   0.03021   0.02546  -0.0030   0.8349   0.0223
  -5.750  -0.4940   0.02884   0.02382  -0.0009   0.7998   0.0232
  -5.500  -0.4750   0.02948   0.02391   0.0022   0.7713   0.0261
  -5.250  -0.4523   0.01992   0.01342   0.0055   0.7548   0.0136
  -5.000  -0.4246   0.01826   0.01155   0.0060   0.7325   0.0120
  -4.750  -0.3944   0.01619   0.00910   0.0063   0.7130   0.0106
  -4.500  -0.3684   0.01518   0.00790   0.0071   0.6948   0.0104
  -4.250  -0.3444   0.01444   0.00704   0.0080   0.6775   0.0104
  -4.000  -0.3221   0.01376   0.00628   0.0091   0.6609   0.0106
  -3.750  -0.3003   0.01324   0.00567   0.0104   0.6454   0.0110
  -3.500  -0.2784   0.01279   0.00514   0.0117   0.6308   0.0116
  -3.250  -0.2557   0.01243   0.00469   0.0128   0.6169   0.0129
  -3.000  -0.2343   0.01197   0.00417   0.0142   0.6035   0.0145
  -2.750  -0.2118   0.01161   0.00375   0.0154   0.5906   0.0193
  -2.500  -0.1924   0.01103   0.00333   0.0171   0.5790   0.0575
  -2.250  -0.1764   0.01031   0.00305   0.0191   0.5683   0.1780
  -2.000  -0.1817   0.00846   0.00255   0.0249   0.5594   0.5168
  -1.750  -0.1837   0.00752   0.00272   0.0316   0.5508   0.7962
  -1.500  -0.1619   0.00787   0.00301   0.0336   0.5399   0.8371
  -1.250  -0.1350   0.00844   0.00359   0.0349   0.5295   0.8589
  -1.000  -0.1077   0.00898   0.00405   0.0360   0.5198   0.8726
  -0.750  -0.0828   0.00932   0.00430   0.0372   0.5097   0.8832
  -0.500  -0.0461   0.00994   0.00486   0.0364   0.4996   0.8895
  -0.250  -0.0212   0.01030   0.00511   0.0376   0.4910   0.8989
   0.000   0.0233   0.01080   0.00555   0.0350   0.4808   0.9022
   0.250   0.0549   0.01091   0.00556   0.0343   0.4725   0.9037
   0.500   0.0834   0.01093   0.00551   0.0342   0.4639   0.9054
   0.750   0.1085   0.01092   0.00542   0.0346   0.4568   0.9076
   1.000   0.1276   0.01081   0.00527   0.0362   0.4497   0.9109
   1.250   0.1435   0.01068   0.00506   0.0384   0.4433   0.9143
   1.500   0.1723   0.01065   0.00499   0.0382   0.4360   0.9152
   1.750   0.1998   0.01068   0.00494   0.0381   0.4295   0.9161
   2.000   0.2281   0.01067   0.00492   0.0379   0.4229   0.9172
   2.250   0.2552   0.01070   0.00489   0.0380   0.4164   0.9184
   2.500   0.2816   0.01071   0.00487   0.0381   0.4106   0.9196
   2.750   0.3081   0.01071   0.00486   0.0382   0.4045   0.9211
   3.000   0.3324   0.01075   0.00483   0.0388   0.3987   0.9228
   3.250   0.3562   0.01070   0.00479   0.0394   0.3932   0.9246
   3.500   0.3782   0.01066   0.00474   0.0404   0.3878   0.9267
   3.750   0.3992   0.01069   0.00470   0.0415   0.3827   0.9290
   4.000   0.4266   0.01065   0.00471   0.0414   0.3772   0.9299
   4.250   0.4536   0.01069   0.00473   0.0414   0.3717   0.9308
   4.500   0.4804   0.01077   0.00478   0.0414   0.3665   0.9318
   4.750   0.5075   0.01079   0.00484   0.0414   0.3609   0.9329
   5.000   0.5339   0.01086   0.00489   0.0415   0.3556   0.9341
   5.250   0.5601   0.01094   0.00498   0.0416   0.3502   0.9356
   5.500   0.5860   0.01098   0.00506   0.0418   0.3446   0.9373
   5.750   0.6102   0.01107   0.00511   0.0422   0.3392   0.9390
   6.000   0.6346   0.01110   0.00519   0.0427   0.3338   0.9408
   6.250   0.6581   0.01113   0.00525   0.0432   0.3279   0.9427
   6.500   0.6823   0.01125   0.00534   0.0436   0.3223   0.9443
   6.750   0.7097   0.01128   0.00545   0.0435   0.3163   0.9454
   7.000   0.7361   0.01140   0.00557   0.0435   0.3101   0.9467
   7.250   0.7628   0.01150   0.00573   0.0434   0.3039   0.9482
   7.500   0.7888   0.01161   0.00587   0.0435   0.2972   0.9500
   7.750   0.8137   0.01175   0.00603   0.0438   0.2906   0.9520
   8.000   0.8381   0.01184   0.00618   0.0441   0.2830   0.9541
   8.250   0.8603   0.01197   0.00633   0.0449   0.2760   0.9567
   8.500   0.8842   0.01208   0.00649   0.0453   0.2682   0.9588
   8.750   0.9113   0.01226   0.00672   0.0450   0.2598   0.9603
   9.000   0.9376   0.01250   0.00696   0.0447   0.2500   0.9621
   9.250   0.9646   0.01269   0.00721   0.0444   0.2399   0.9639
   9.500   0.9897   0.01294   0.00750   0.0444   0.2294   0.9663
   9.750   1.0120   0.01323   0.00780   0.0449   0.2176   0.9696
  10.000   1.0350   0.01356   0.00814   0.0452   0.2046   0.9726
  10.250   1.0631   0.01401   0.00859   0.0443   0.1887   0.9742
  10.500   1.0896   0.01458   0.00913   0.0435   0.1703   0.9761
  10.750   1.1136   0.01527   0.00976   0.0430   0.1516   0.9786
  11.000   1.1363   0.01594   0.01041   0.0428   0.1352   0.9819
  11.250   1.1591   0.01672   0.01117   0.0423   0.1189   0.9847
  11.500   1.1839   0.01773   0.01213   0.0411   0.1023   0.9867
  11.750   1.2056   0.01876   0.01314   0.0403   0.0883   0.9901
  12.000   1.2238   0.01980   0.01417   0.0400   0.0768   0.9947
  12.250   1.2430   0.02106   0.01544   0.0389   0.0654   0.9992
  12.500   1.2180   0.02149   0.01592   0.0466   0.0645   1.0000
  12.750   1.2133   0.02260   0.01706   0.0498   0.0597   1.0000
  13.000   1.2077   0.02443   0.01890   0.0518   0.0544   1.0000
  13.250   1.2082   0.02622   0.02075   0.0527   0.0499   1.0000
  13.500   1.2015   0.02889   0.02345   0.0532   0.0455   1.0000
  13.750   1.2015   0.03118   0.02585   0.0533   0.0423   1.0000
  14.000   1.1947   0.03430   0.02900   0.0531   0.0389   1.0000
  14.250   1.1858   0.03777   0.03254   0.0526   0.0365   1.0000
  14.500   1.1828   0.04071   0.03557   0.0521   0.0339   1.0000
  14.750   1.1742   0.04432   0.03924   0.0513   0.0320   1.0000
  15.000   1.1591   0.04873   0.04372   0.0503   0.0303   1.0000
  15.250   1.1521   0.05230   0.04737   0.0494   0.0291   1.0000
  15.500   1.1437   0.05610   0.05128   0.0484   0.0277   1.0000
  15.750   1.1350   0.06010   0.05536   0.0471   0.0265   1.0000
  16.000   1.1257   0.06431   0.05962   0.0457   0.0255   1.0000
  16.250   1.1116   0.06926   0.06463   0.0440   0.0243   1.0000
  16.500   1.1006   0.07390   0.06935   0.0423   0.0234   1.0000
  16.750   1.0966   0.07769   0.07324   0.0409   0.0226   1.0000
  17.000   1.0911   0.08175   0.07739   0.0393   0.0218   1.0000
  17.250   1.0851   0.08600   0.08171   0.0375   0.0208   1.0000
  17.500   1.0764   0.09070   0.08646   0.0355   0.0200   1.0000
  17.750   1.0669   0.09555   0.09135   0.0334   0.0192   1.0000
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