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EPPLER STE 871-514 AIRFOIL (ste87151-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EPPLER STE 871-514 AIRFOIL (ste87151-il)
Reynolds number: 1,000,000
Max Cl/Cd: 113.92 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ste87151-il-1000000.txt
Download as CSV file: xf-ste87151-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER STE 871-514 AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.2879   0.08333   0.08124  -0.1043   0.9116   0.0102
 -10.750  -0.2944   0.07636   0.07428  -0.1093   0.9105   0.0104
 -10.500  -0.3099   0.06621   0.06411  -0.1192   0.9094   0.0102
 -10.250  -0.3308   0.05911   0.05690  -0.1242   0.9082   0.0101
 -10.000  -0.3490   0.05387   0.05154  -0.1261   0.9069   0.0102
  -9.750  -0.3809   0.03018   0.02733  -0.1238   0.9043   0.0114
  -9.500  -0.3776   0.02832   0.02539  -0.1230   0.9037   0.0115
  -9.250  -0.3697   0.02670   0.02370  -0.1224   0.9031   0.0117
  -9.000  -0.3584   0.02544   0.02238  -0.1219   0.9024   0.0119
  -8.750  -0.3489   0.02341   0.02021  -0.1211   0.9014   0.0123
  -8.250  -0.3645   0.02295   0.01834  -0.1177   0.8995   0.0116
  -8.000  -0.3424   0.02130   0.01659  -0.1172   0.8989   0.0106
  -7.750  -0.3216   0.01933   0.01437  -0.1165   0.8983   0.0103
  -7.500  -0.2986   0.01779   0.01263  -0.1160   0.8977   0.0101
  -7.250  -0.2745   0.01686   0.01157  -0.1156   0.8972   0.0103
  -7.000  -0.2501   0.01603   0.01064  -0.1153   0.8967   0.0105
  -6.750  -0.2263   0.01518   0.00970  -0.1148   0.8961   0.0104
  -6.500  -0.2029   0.01445   0.00891  -0.1143   0.8954   0.0104
  -6.250  -0.1797   0.01386   0.00827  -0.1138   0.8947   0.0106
  -6.000  -0.1564   0.01340   0.00777  -0.1133   0.8941   0.0108
  -5.750  -0.1321   0.01306   0.00739  -0.1129   0.8934   0.0111
  -5.500  -0.1099   0.01245   0.00675  -0.1123   0.8925   0.0119
  -5.250  -0.0841   0.01221   0.00650  -0.1122   0.8915   0.0128
  -5.000  -0.0591   0.01211   0.00637  -0.1120   0.8902   0.0137
  -4.750  -0.0363   0.01187   0.00613  -0.1114   0.8893   0.0147
  -4.500  -0.0126   0.01171   0.00598  -0.1109   0.8883   0.0159
  -4.250   0.0104   0.01157   0.00584  -0.1103   0.8871   0.0174
  -4.000   0.0336   0.01149   0.00577  -0.1097   0.8858   0.0200
  -3.750   0.0568   0.01134   0.00565  -0.1091   0.8843   0.0252
  -3.500   0.0805   0.01116   0.00554  -0.1086   0.8830   0.0389
  -3.250   0.1022   0.01062   0.00540  -0.1081   0.8817   0.1387
  -3.000   0.1245   0.00980   0.00520  -0.1081   0.8805   0.3166
  -2.750   0.1499   0.00845   0.00483  -0.1091   0.8794   0.6001
  -2.500   0.1784   0.00830   0.00505  -0.1094   0.8785   0.7259
  -2.250   0.2080   0.00846   0.00520  -0.1097   0.8777   0.7442
  -2.000   0.2369   0.00867   0.00542  -0.1097   0.8769   0.7549
  -1.750   0.2658   0.00903   0.00576  -0.1097   0.8762   0.7670
  -1.500   0.2925   0.00930   0.00609  -0.1092   0.8754   0.7740
  -1.250   0.3208   0.00956   0.00635  -0.1092   0.8744   0.7787
  -1.000   0.3441   0.00977   0.00655  -0.1083   0.8721   0.7829
  -0.750   0.3683   0.00978   0.00656  -0.1077   0.8690   0.7862
  -0.500   0.3965   0.00967   0.00647  -0.1077   0.8668   0.7886
  -0.250   0.4282   0.00948   0.00627  -0.1084   0.8648   0.7902
   0.000   0.4626   0.00918   0.00595  -0.1097   0.8629   0.7914
   0.250   0.4976   0.00886   0.00561  -0.1112   0.8609   0.7924
   0.500   0.5339   0.00859   0.00530  -0.1129   0.8587   0.7933
   0.750   0.5606   0.00845   0.00518  -0.1128   0.8551   0.7944
   1.000   0.5878   0.00823   0.00496  -0.1126   0.8504   0.7956
   1.250   0.6208   0.00789   0.00460  -0.1137   0.8461   0.7966
   1.500   0.6535   0.00753   0.00421  -0.1147   0.8401   0.7974
   1.750   0.6779   0.00733   0.00403  -0.1140   0.8322   0.7985
   2.000   0.7082   0.00713   0.00380  -0.1146   0.8265   0.7992
   2.250   0.7302   0.00707   0.00379  -0.1135   0.8175   0.7999
   2.500   0.7551   0.00697   0.00369  -0.1130   0.8052   0.8007
   2.750   0.7781   0.00683   0.00347  -0.1119   0.7726   0.8014
   3.000   0.7858   0.00715   0.00342  -0.1076   0.7039   0.8019
   3.250   0.7800   0.00774   0.00368  -0.1006   0.6413   0.8025
   3.500   0.7889   0.00818   0.00392  -0.0971   0.5965   0.8036
   3.750   0.7938   0.00893   0.00435  -0.0929   0.5254   0.8047
   4.000   0.8020   0.00966   0.00478  -0.0895   0.4607   0.8054
   4.250   0.8127   0.01036   0.00518  -0.0866   0.3965   0.8060
   4.500   0.8260   0.01102   0.00557  -0.0843   0.3370   0.8065
   4.750   0.8407   0.01165   0.00594  -0.0823   0.2818   0.8071
   5.000   0.8566   0.01225   0.00629  -0.0805   0.2327   0.8076
   5.250   0.8742   0.01278   0.00663  -0.0791   0.1923   0.8081
   5.500   0.8925   0.01330   0.00698  -0.0778   0.1584   0.8085
   5.750   0.9110   0.01380   0.00733  -0.0766   0.1304   0.8091
   6.000   0.9303   0.01427   0.00768  -0.0754   0.1087   0.8097
   6.250   0.9504   0.01469   0.00801  -0.0744   0.0931   0.8104
   6.500   0.9711   0.01508   0.00836  -0.0736   0.0824   0.8109
   6.750   0.9920   0.01546   0.00870  -0.0727   0.0749   0.8113
   7.000   1.0127   0.01585   0.00906  -0.0719   0.0693   0.8118
   7.250   1.0334   0.01623   0.00942  -0.0710   0.0649   0.8123
   7.500   1.0545   0.01659   0.00979  -0.0703   0.0616   0.8127
   7.750   1.0745   0.01703   0.01021  -0.0693   0.0585   0.8132
   8.000   1.0958   0.01737   0.01059  -0.0686   0.0562   0.8137
   8.250   1.1157   0.01780   0.01101  -0.0677   0.0540   0.8142
   8.500   1.1354   0.01823   0.01147  -0.0667   0.0521   0.8146
   8.750   1.1554   0.01864   0.01190  -0.0658   0.0503   0.8151
   9.000   1.1736   0.01917   0.01243  -0.0647   0.0487   0.8156
   9.250   1.1926   0.01964   0.01294  -0.0636   0.0474   0.8161
   9.500   1.2121   0.02008   0.01342  -0.0627   0.0461   0.8165
   9.750   1.2304   0.02058   0.01394  -0.0616   0.0449   0.8170
  10.000   1.2455   0.02129   0.01466  -0.0601   0.0436   0.8174
  10.250   1.2642   0.02177   0.01520  -0.0590   0.0427   0.8179
  10.500   1.2821   0.02229   0.01577  -0.0579   0.0417   0.8183
  10.750   1.2998   0.02282   0.01632  -0.0569   0.0406   0.8188
  11.000   1.3139   0.02358   0.01710  -0.0553   0.0393   0.8193
  11.250   1.3332   0.02402   0.01759  -0.0545   0.0381   0.8197
  11.500   1.3503   0.02459   0.01821  -0.0534   0.0371   0.8202
  11.750   1.3661   0.02526   0.01890  -0.0521   0.0362   0.8208
  12.000   1.3789   0.02611   0.01979  -0.0505   0.0353   0.8217
  12.250   1.3962   0.02665   0.02041  -0.0495   0.0344   0.8225
  12.500   1.4120   0.02728   0.02109  -0.0483   0.0335   0.8232
  12.750   1.4269   0.02799   0.02185  -0.0471   0.0326   0.8240
  13.000   1.4376   0.02899   0.02288  -0.0453   0.0318   0.8247
  13.250   1.4533   0.02965   0.02363  -0.0442   0.0310   0.8255
  13.500   1.4686   0.03033   0.02438  -0.0432   0.0300   0.8262
  13.750   1.4831   0.03108   0.02516  -0.0420   0.0289   0.8270
  14.000   1.4950   0.03204   0.02616  -0.0406   0.0279   0.8277
  14.250   1.5108   0.03272   0.02693  -0.0397   0.0268   0.8285
  14.500   1.5243   0.03357   0.02782  -0.0386   0.0257   0.8293
  14.750   1.5356   0.03460   0.02890  -0.0372   0.0246   0.8302
  15.000   1.5490   0.03547   0.02984  -0.0362   0.0235   0.8310
  15.250   1.5600   0.03653   0.03095  -0.0349   0.0223   0.8319
  15.500   1.5703   0.03768   0.03217  -0.0337   0.0213   0.8327
  15.750   1.5806   0.03886   0.03342  -0.0325   0.0200   0.8336
  16.000   1.5887   0.04025   0.03485  -0.0312   0.0188   0.8345
  16.250   1.5975   0.04162   0.03630  -0.0300   0.0175   0.8353
  16.500   1.6032   0.04327   0.03799  -0.0287   0.0162   0.8361
  16.750   1.6089   0.04496   0.03977  -0.0275   0.0150   0.8369
  17.000   1.6116   0.04699   0.04184  -0.0262   0.0138   0.8376
  17.250   1.6148   0.04903   0.04398  -0.0252   0.0128   0.8390
  17.500   1.6150   0.05142   0.04645  -0.0241   0.0119   0.8404
  17.750   1.6137   0.05403   0.04916  -0.0231   0.0112   0.8418
  18.000   1.6128   0.05670   0.05194  -0.0223   0.0105   0.8432
  18.250   1.6091   0.05977   0.05512  -0.0217   0.0100   0.8445
  18.500   1.6022   0.06335   0.05881  -0.0213   0.0094   0.8458
  18.750   1.5971   0.06683   0.06241  -0.0212   0.0091   0.8472
  19.000   1.5909   0.07054   0.06624  -0.0214   0.0087   0.8486
  19.250   1.5821   0.07469   0.07052  -0.0218   0.0084   0.8499
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