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EPPLER STE 871-514 AIRFOIL (ste87151-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: EPPLER STE 871-514 AIRFOIL (ste87151-il)
Reynolds number: 500,000
Max Cl/Cd: 79.06 at α=2.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ste87151-il-500000-n5.txt
Download as CSV file: xf-ste87151-il-500000-n5.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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.3007   0.08795   0.08505  -0.1017   0.9075   0.0080
 -11.250  -0.3058   0.08197   0.07909  -0.1053   0.9066   0.0080
 -11.000  -0.3141   0.07464   0.07178  -0.1106   0.9057   0.0078
 -10.750  -0.3355   0.06360   0.06066  -0.1206   0.9044   0.0076
 -10.500  -0.3581   0.05677   0.05369  -0.1244   0.9031   0.0075
 -10.250  -0.3780   0.05130   0.04807  -0.1258   0.9018   0.0074
 -10.000  -0.3959   0.04632   0.04289  -0.1257   0.9002   0.0073
  -9.750  -0.4126   0.04142   0.03771  -0.1241   0.8986   0.0071
  -9.500  -0.4303   0.03447   0.03025  -0.1213   0.8969   0.0069
  -9.250  -0.4386   0.02814   0.02324  -0.1183   0.8954   0.0069
  -9.000  -0.4272   0.02530   0.02001  -0.1168   0.8944   0.0070
  -8.750  -0.4103   0.02332   0.01772  -0.1158   0.8934   0.0071
  -8.500  -0.3906   0.02177   0.01593  -0.1151   0.8927   0.0073
  -8.250  -0.3692   0.02047   0.01441  -0.1145   0.8921   0.0075
  -8.000  -0.3468   0.01941   0.01317  -0.1140   0.8916   0.0078
  -7.750  -0.3238   0.01852   0.01214  -0.1136   0.8910   0.0080
  -7.500  -0.3005   0.01778   0.01127  -0.1132   0.8905   0.0083
  -7.250  -0.2769   0.01717   0.01056  -0.1128   0.8900   0.0085
  -7.000  -0.2544   0.01645   0.00977  -0.1123   0.8895   0.0087
  -6.750  -0.2314   0.01592   0.00921  -0.1119   0.8889   0.0091
  -6.500  -0.2071   0.01559   0.00886  -0.1117   0.8884   0.0096
  -6.250  -0.1831   0.01527   0.00851  -0.1114   0.8876   0.0102
  -6.000  -0.1614   0.01496   0.00817  -0.1107   0.8868   0.0107
  -5.750  -0.1405   0.01466   0.00784  -0.1098   0.8859   0.0112
  -5.500  -0.1202   0.01437   0.00753  -0.1087   0.8847   0.0116
  -5.250  -0.1002   0.01410   0.00725  -0.1076   0.8832   0.0122
  -5.000  -0.0788   0.01392   0.00707  -0.1068   0.8820   0.0130
  -4.750  -0.0567   0.01375   0.00688  -0.1060   0.8808   0.0140
  -4.500  -0.0331   0.01352   0.00663  -0.1054   0.8794   0.0153
  -4.250  -0.0082   0.01330   0.00642  -0.1052   0.8781   0.0178
  -4.000   0.0176   0.01307   0.00619  -0.1051   0.8770   0.0214
  -3.750   0.0441   0.01283   0.00595  -0.1051   0.8760   0.0270
  -3.500   0.0705   0.01260   0.00576  -0.1052   0.8752   0.0382
  -3.250   0.0958   0.01223   0.00559  -0.1052   0.8745   0.0870
  -3.000   0.1196   0.01152   0.00537  -0.1053   0.8737   0.2203
  -2.750   0.1429   0.01033   0.00504  -0.1059   0.8729   0.4556
  -2.500   0.1569   0.00980   0.00547  -0.1037   0.8704   0.6859
  -2.250   0.1763   0.01020   0.00589  -0.1020   0.8672   0.7298
  -2.000   0.2009   0.01059   0.00626  -0.1011   0.8651   0.7550
  -1.750   0.2263   0.01095   0.00660  -0.1004   0.8636   0.7684
  -1.500   0.2512   0.01117   0.00685  -0.0996   0.8624   0.7730
  -1.250   0.2789   0.01128   0.00694  -0.0995   0.8615   0.7772
  -1.000   0.3092   0.01127   0.00689  -0.1002   0.8606   0.7802
  -0.750   0.3409   0.01121   0.00678  -0.1012   0.8598   0.7824
  -0.500   0.3725   0.01114   0.00668  -0.1022   0.8590   0.7838
  -0.250   0.4044   0.01103   0.00655  -0.1032   0.8582   0.7846
   0.250   0.4432   0.01118   0.00673  -0.1000   0.8494   0.7869
   0.500   0.4755   0.01093   0.00648  -0.1009   0.8472   0.7877
   0.750   0.5115   0.01058   0.00611  -0.1026   0.8451   0.7883
   1.000   0.5490   0.01020   0.00571  -0.1045   0.8431   0.7890
   1.250   0.5606   0.01027   0.00582  -0.1013   0.8349   0.7902
   1.500   0.5930   0.00990   0.00545  -0.1022   0.8304   0.7908
   1.750   0.6061   0.00989   0.00547  -0.0992   0.8211   0.7921
   2.000   0.6182   0.00985   0.00545  -0.0960   0.8098   0.7932
   2.250   0.6302   0.01002   0.00563  -0.0931   0.7908   0.7942
   2.500   0.6870   0.00869   0.00394  -0.0979   0.7248   0.7941
   2.750   0.6961   0.00920   0.00398  -0.0940   0.6443   0.7952
   3.000   0.7055   0.00978   0.00430  -0.0906   0.5965   0.7963
   3.250   0.7118   0.01054   0.00474  -0.0867   0.5307   0.7972
   3.500   0.7215   0.01125   0.00518  -0.0836   0.4742   0.7979
   3.750   0.7344   0.01191   0.00558  -0.0813   0.4219   0.7985
   4.000   0.7483   0.01255   0.00597  -0.0791   0.3691   0.7991
   4.250   0.7630   0.01319   0.00635  -0.0771   0.3152   0.7996
   4.500   0.7790   0.01380   0.00673  -0.0754   0.2650   0.8002
   4.750   0.7968   0.01435   0.00709  -0.0740   0.2247   0.8009
   5.000   0.8154   0.01486   0.00745  -0.0728   0.1900   0.8014
   5.250   0.8344   0.01537   0.00780  -0.0717   0.1590   0.8019
   5.500   0.8540   0.01585   0.00816  -0.0707   0.1336   0.8024
   5.750   0.8740   0.01631   0.00852  -0.0697   0.1138   0.8029
   6.000   0.8946   0.01673   0.00888  -0.0688   0.0996   0.8034
   6.250   0.9155   0.01712   0.00924  -0.0680   0.0890   0.8039
   6.500   0.9365   0.01752   0.00961  -0.0673   0.0811   0.8044
   6.750   0.9569   0.01795   0.01002  -0.0664   0.0737   0.8049
   7.000   0.9780   0.01833   0.01041  -0.0657   0.0689   0.8054
   7.250   0.9985   0.01875   0.01082  -0.0648   0.0643   0.8060
   7.500   1.0186   0.01920   0.01128  -0.0640   0.0605   0.8065
   7.750   1.0394   0.01959   0.01172  -0.0632   0.0584   0.8070
   8.000   1.0595   0.02003   0.01218  -0.0623   0.0560   0.8076
   8.250   1.0790   0.02051   0.01267  -0.0614   0.0537   0.8082
   8.500   1.0975   0.02105   0.01323  -0.0603   0.0514   0.8090
   8.750   1.1163   0.02157   0.01379  -0.0593   0.0497   0.8097
   9.000   1.1358   0.02204   0.01432  -0.0584   0.0483   0.8104
   9.250   1.1545   0.02256   0.01489  -0.0574   0.0470   0.8109
   9.500   1.1726   0.02312   0.01550  -0.0563   0.0456   0.8115
   9.750   1.1901   0.02371   0.01613  -0.0552   0.0444   0.8120
  10.000   1.2070   0.02435   0.01681  -0.0540   0.0431   0.8126
  10.250   1.2223   0.02511   0.01760  -0.0526   0.0419   0.8131
  10.500   1.2367   0.02592   0.01847  -0.0511   0.0409   0.8136
  10.750   1.2534   0.02655   0.01918  -0.0499   0.0402   0.8141
  11.000   1.2698   0.02719   0.01991  -0.0488   0.0394   0.8147
  11.250   1.2853   0.02791   0.02071  -0.0475   0.0386   0.8153
  11.500   1.3000   0.02867   0.02156  -0.0461   0.0378   0.8159
  11.750   1.3151   0.02941   0.02237  -0.0449   0.0367   0.8166
  12.000   1.3303   0.03014   0.02314  -0.0437   0.0354   0.8172
  12.250   1.3429   0.03106   0.02410  -0.0423   0.0340   0.8179
  12.500   1.3542   0.03209   0.02520  -0.0407   0.0330   0.8185
  12.750   1.3681   0.03293   0.02615  -0.0394   0.0325   0.8193
  13.000   1.3811   0.03386   0.02718  -0.0381   0.0317   0.8200
  13.250   1.3937   0.03481   0.02823  -0.0369   0.0309   0.8207
  13.500   1.4062   0.03578   0.02930  -0.0356   0.0300   0.8215
  13.750   1.4180   0.03682   0.03041  -0.0344   0.0291   0.8223
  14.000   1.4286   0.03797   0.03162  -0.0331   0.0283   0.8231
  14.250   1.4373   0.03931   0.03302  -0.0317   0.0274   0.8240
  14.500   1.4448   0.04077   0.03457  -0.0303   0.0267   0.8248
  14.750   1.4550   0.04203   0.03596  -0.0291   0.0260   0.8257
  15.000   1.4646   0.04337   0.03741  -0.0280   0.0252   0.8267
  15.250   1.4735   0.04478   0.03893  -0.0270   0.0242   0.8277
  15.500   1.4824   0.04625   0.04048  -0.0261   0.0231   0.8287
  15.750   1.4891   0.04794   0.04223  -0.0251   0.0221   0.8297
  16.000   1.4947   0.04978   0.04418  -0.0241   0.0212   0.8306
  16.250   1.5013   0.05155   0.04609  -0.0233   0.0200   0.8316
  16.500   1.5070   0.05346   0.04809  -0.0226   0.0187   0.8326
  16.750   1.5106   0.05564   0.05034  -0.0219   0.0176   0.8337
  17.000   1.5125   0.05807   0.05289  -0.0213   0.0167   0.8348
  17.250   1.5137   0.06065   0.05560  -0.0209   0.0156   0.8359
  17.500   1.5131   0.06354   0.05860  -0.0206   0.0147   0.8371
  18.000   1.5065   0.07023   0.06554  -0.0207   0.0131   0.8394
  18.250   1.5010   0.07400   0.06944  -0.0210   0.0124   0.8406
  18.500   1.4935   0.07818   0.07375  -0.0217   0.0119   0.8418
  18.750   1.4840   0.08282   0.07852  -0.0227   0.0115   0.8429
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