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EPPLER 417 AIRFOIL (e417-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 417 AIRFOIL (e417-il)
Reynolds number: 200,000
Max Cl/Cd: 66.14 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e417-il-200000-n5.txt
Download as CSV file: xf-e417-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 417 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.4949   0.10518   0.10156  -0.0579   0.9901   0.0159
 -11.500  -0.5809   0.07595   0.07199  -0.0767   0.9875   0.0141
 -11.250  -0.6044   0.06864   0.06438  -0.0822   0.9856   0.0138
 -10.750  -0.6348   0.06052   0.05587  -0.0847   0.9790   0.0136
 -10.500  -0.6468   0.05659   0.05173  -0.0860   0.9762   0.0136
 -10.250  -0.6548   0.05338   0.04834  -0.0866   0.9736   0.0135
 -10.000  -0.6701   0.05113   0.04597  -0.0840   0.9681   0.0135
  -9.750  -0.6763   0.04824   0.04285  -0.0838   0.9645   0.0134
  -9.500  -0.6686   0.04497   0.03927  -0.0853   0.9623   0.0134
  -9.250  -0.6755   0.04268   0.03673  -0.0821   0.9566   0.0134
  -9.000  -0.6659   0.04009   0.03384  -0.0817   0.9538   0.0134
  -8.750  -0.6493   0.03754   0.03093  -0.0822   0.9517   0.0134
  -8.500  -0.6280   0.03535   0.02843  -0.0829   0.9503   0.0134
  -8.250  -0.6138   0.03374   0.02656  -0.0817   0.9477   0.0135
  -8.000  -0.6010   0.03220   0.02482  -0.0799   0.9444   0.0137
  -7.750  -0.5811   0.03057   0.02304  -0.0793   0.9422   0.0138
  -7.500  -0.5591   0.02916   0.02154  -0.0790   0.9405   0.0141
  -7.250  -0.5355   0.02801   0.02030  -0.0790   0.9391   0.0144
  -7.000  -0.5100   0.02698   0.01920  -0.0794   0.9378   0.0148
  -6.750  -0.4821   0.02613   0.01830  -0.0803   0.9367   0.0159
  -6.500  -0.4670   0.02541   0.01752  -0.0787   0.9332   0.0165
  -6.250  -0.4477   0.02464   0.01669  -0.0779   0.9300   0.0171
  -6.000  -0.4226   0.02379   0.01576  -0.0783   0.9277   0.0174
  -5.750  -0.3945   0.02297   0.01486  -0.0794   0.9259   0.0179
  -5.500  -0.3640   0.02211   0.01394  -0.0811   0.9246   0.0185
  -5.250  -0.3315   0.02135   0.01310  -0.0832   0.9235   0.0195
  -5.000  -0.2977   0.02079   0.01244  -0.0852   0.9226   0.0210
  -4.750  -0.2793   0.02044   0.01202  -0.0841   0.9181   0.0226
  -4.500  -0.2510   0.01995   0.01152  -0.0850   0.9154   0.0281
  -4.250  -0.2184   0.01928   0.01096  -0.0870   0.9135   0.0534
  -4.000  -0.1764   0.01740   0.01006  -0.0929   0.9131   0.2622
  -3.750  -0.1377   0.01637   0.01015  -0.0968   0.9123   0.5133
  -3.500  -0.1059   0.01669   0.01052  -0.0974   0.9106   0.5672
  -3.250  -0.0741   0.01720   0.01100  -0.0977   0.9090   0.5966
  -3.000  -0.0548   0.01759   0.01137  -0.0958   0.9042   0.6096
  -2.750  -0.0293   0.01771   0.01144  -0.0953   0.9005   0.6140
  -2.500   0.0018   0.01771   0.01136  -0.0961   0.8982   0.6172
  -2.250   0.0354   0.01764   0.01120  -0.0975   0.8964   0.6209
  -2.000   0.0716   0.01750   0.01093  -0.0995   0.8951   0.6252
  -1.750   0.0935   0.01756   0.01096  -0.0986   0.8900   0.6275
  -1.500   0.1208   0.01754   0.01092  -0.0986   0.8860   0.6296
  -1.250   0.1531   0.01746   0.01080  -0.0996   0.8835   0.6322
  -1.000   0.1879   0.01733   0.01064  -0.1012   0.8818   0.6351
  -0.750   0.2245   0.01715   0.01041  -0.1032   0.8804   0.6382
  -0.500   0.2433   0.01723   0.01044  -0.1018   0.8725   0.6416
  -0.250   0.2754   0.01709   0.01032  -0.1027   0.8695   0.6434
   0.000   0.3106   0.01688   0.01012  -0.1041   0.8675   0.6454
   0.500   0.3646   0.01674   0.01000  -0.1040   0.8565   0.6504
   0.750   0.4008   0.01643   0.00970  -0.1057   0.8539   0.6534
   1.000   0.4389   0.01605   0.00930  -0.1077   0.8515   0.6563
   1.250   0.4580   0.01609   0.00940  -0.1061   0.8419   0.6582
   1.500   0.4919   0.01578   0.00915  -0.1071   0.8390   0.6602
   1.750   0.5142   0.01580   0.00923  -0.1061   0.8307   0.6625
   2.000   0.5461   0.01554   0.00902  -0.1069   0.8258   0.6648
   2.250   0.5727   0.01539   0.00891  -0.1066   0.8168   0.6674
   2.500   0.6081   0.01497   0.00854  -0.1079   0.8095   0.6703
   2.750   0.6345   0.01485   0.00846  -0.1076   0.7975   0.6729
   3.000   0.6641   0.01464   0.00834  -0.1078   0.7863   0.6748
   3.250   0.6980   0.01432   0.00809  -0.1087   0.7736   0.6768
   3.500   0.7359   0.01393   0.00775  -0.1104   0.7569   0.6789
   3.750   0.7823   0.01344   0.00727  -0.1138   0.7339   0.6814
   4.000   0.8279   0.01315   0.00692  -0.1171   0.6992   0.6842
   4.250   0.8681   0.01317   0.00675  -0.1195   0.6527   0.6871
   4.500   0.8936   0.01351   0.00689  -0.1189   0.6022   0.6890
   4.750   0.9107   0.01400   0.00719  -0.1168   0.5533   0.6909
   5.000   0.9228   0.01462   0.00758  -0.1137   0.4989   0.6931
   5.250   0.9310   0.01541   0.00805  -0.1101   0.4365   0.6956
   5.500   0.9379   0.01634   0.00861  -0.1065   0.3680   0.6985
   5.750   0.9485   0.01725   0.00919  -0.1038   0.3052   0.7015
   6.000   0.9619   0.01807   0.00978  -0.1016   0.2532   0.7038
   6.250   0.9759   0.01889   0.01039  -0.0995   0.2055   0.7058
   6.500   0.9897   0.01983   0.01107  -0.0975   0.1551   0.7080
   6.750   1.0047   0.02075   0.01176  -0.0958   0.1117   0.7105
   7.000   1.0198   0.02173   0.01252  -0.0941   0.0737   0.7133
   7.250   1.0356   0.02269   0.01335  -0.0926   0.0445   0.7164
   7.500   1.0509   0.02368   0.01425  -0.0909   0.0266   0.7190
   7.750   1.0670   0.02454   0.01515  -0.0892   0.0208   0.7212
   8.000   1.0837   0.02537   0.01606  -0.0876   0.0183   0.7236
   8.250   1.1003   0.02621   0.01699  -0.0861   0.0164   0.7263
   8.500   1.1157   0.02719   0.01806  -0.0846   0.0152   0.7292
   8.750   1.1315   0.02812   0.01912  -0.0831   0.0144   0.7324
   9.000   1.1456   0.02912   0.02027  -0.0813   0.0138   0.7350
   9.250   1.1585   0.03020   0.02149  -0.0794   0.0134   0.7377
   9.500   1.1706   0.03138   0.02279  -0.0775   0.0130   0.7406
   9.750   1.1820   0.03265   0.02418  -0.0756   0.0127   0.7436
  10.000   1.1923   0.03406   0.02571  -0.0737   0.0123   0.7466
  10.250   1.2016   0.03558   0.02735  -0.0718   0.0121   0.7494
  10.500   1.2096   0.03725   0.02914  -0.0697   0.0118   0.7520
  10.750   1.2175   0.03913   0.03113  -0.0678   0.0116   0.7550
  11.000   1.2276   0.04091   0.03304  -0.0662   0.0115   0.7585
  11.250   1.2387   0.04264   0.03492  -0.0647   0.0113   0.7620
  11.500   1.2489   0.04442   0.03690  -0.0632   0.0111   0.7650
  11.750   1.2582   0.04631   0.03899  -0.0617   0.0108   0.7680
  12.000   1.2662   0.04833   0.04124  -0.0603   0.0106   0.7713
  12.250   1.2728   0.05051   0.04363  -0.0589   0.0102   0.7749
  12.500   1.2781   0.05290   0.04622  -0.0576   0.0100   0.7786
  12.750   1.2811   0.05550   0.04905  -0.0561   0.0099   0.7818
  13.000   1.2821   0.05835   0.05214  -0.0548   0.0098   0.7855
  13.250   1.2810   0.06149   0.05552  -0.0537   0.0097   0.7894
  13.750   1.2716   0.06868   0.06321  -0.0521   0.0096   0.7966
  14.000   1.2636   0.07282   0.06761  -0.0518   0.0095   0.8002
  14.250   1.2537   0.07742   0.07247  -0.0521   0.0095   0.8040
  14.500   1.2417   0.08257   0.07787  -0.0530   0.0095   0.8079
  14.750   1.2275   0.08823   0.08380  -0.0545   0.0095   0.8113
  15.000   1.2117   0.09457   0.09041  -0.0568   0.0095   0.8153
  15.250   1.1939   0.10173   0.09783  -0.0601   0.0095   0.8194
  15.750   1.1531   0.11875   0.11537  -0.0700   0.0096   0.8269
  16.000   1.1287   0.12935   0.12622  -0.0770   0.0097   0.8302
  16.250   1.1002   0.14219   0.13931  -0.0858   0.0098   0.8324
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