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EPPLER EC 86(-3)-914 AIRFOIL (ec863914-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER EC 86(-3)-914 AIRFOIL (ec863914-il)
Reynolds number: 200,000
Max Cl/Cd: 63.04 at α=3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ec863914-il-200000-n5.txt
Download as CSV file: xf-ec863914-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER EC 86(-3)-914 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  -0.3517   0.09628   0.09252  -0.0877   0.9662   0.0102
 -11.500  -0.3788   0.08542   0.08157  -0.0943   0.9646   0.0100
 -11.250  -0.3967   0.07654   0.07255  -0.1014   0.9630   0.0099
 -11.000  -0.4118   0.06884   0.06468  -0.1084   0.9617   0.0098
 -10.750  -0.4347   0.06504   0.06083  -0.1079   0.9577   0.0099
 -10.500  -0.4530   0.06010   0.05573  -0.1106   0.9540   0.0097
 -10.250  -0.4655   0.05592   0.05136  -0.1132   0.9514   0.0096
 -10.000  -0.4773   0.05181   0.04702  -0.1158   0.9493   0.0095
  -9.750  -0.5055   0.05055   0.04573  -0.1101   0.9428   0.0096
  -9.500  -0.5199   0.04805   0.04303  -0.1089   0.9386   0.0094
  -9.250  -0.5181   0.04453   0.03915  -0.1113   0.9362   0.0092
  -9.000  -0.5320   0.04284   0.03730  -0.1076   0.9297   0.0092
  -8.750  -0.5215   0.03996   0.03401  -0.1088   0.9265   0.0089
  -8.500  -0.5011   0.03760   0.03134  -0.1102   0.9247   0.0088
  -8.250  -0.4776   0.03550   0.02902  -0.1118   0.9235   0.0090
  -8.000  -0.4646   0.03412   0.02755  -0.1109   0.9201   0.0095
  -7.750  -0.4481   0.03280   0.02608  -0.1103   0.9168   0.0098
  -7.500  -0.4237   0.03141   0.02452  -0.1109   0.9148   0.0100
  -7.250  -0.3966   0.03007   0.02301  -0.1118   0.9133   0.0100
  -7.000  -0.3675   0.02881   0.02163  -0.1129   0.9122   0.0099
  -6.750  -0.3364   0.02763   0.02035  -0.1144   0.9112   0.0097
  -6.500  -0.3093   0.02670   0.01933  -0.1152   0.9093   0.0096
  -6.250  -0.2886   0.02590   0.01847  -0.1149   0.9053   0.0096
  -6.000  -0.2566   0.02506   0.01754  -0.1168   0.9035   0.0095
  -5.750  -0.2215   0.02427   0.01661  -0.1192   0.9021   0.0095
  -5.500  -0.1855   0.02362   0.01584  -0.1216   0.9010   0.0095
  -5.250  -0.1486   0.02306   0.01514  -0.1241   0.9000   0.0094
  -5.000  -0.1117   0.02257   0.01452  -0.1264   0.8992   0.0095
  -4.750  -0.0890   0.02233   0.01419  -0.1259   0.8948   0.0095
  -4.500  -0.0577   0.02202   0.01378  -0.1270   0.8923   0.0096
  -4.250  -0.0236   0.02173   0.01339  -0.1285   0.8905   0.0097
  -4.000   0.0119   0.02145   0.01300  -0.1303   0.8891   0.0099
  -3.750   0.0482   0.02120   0.01268  -0.1322   0.8880   0.0101
  -3.500   0.0730   0.02112   0.01255  -0.1319   0.8837   0.0104
  -3.250   0.1031   0.02097   0.01237  -0.1326   0.8804   0.0109
  -3.000   0.1483   0.01996   0.01200  -0.1375   0.8796   0.1526
  -2.750   0.1841   0.01978   0.01183  -0.1392   0.8779   0.1711
  -2.500   0.2215   0.01955   0.01168  -0.1413   0.8766   0.1980
  -2.250   0.2465   0.01950   0.01170  -0.1412   0.8711   0.2197
  -2.000   0.2838   0.01912   0.01161  -0.1437   0.8683   0.2745
  -1.750   0.3271   0.01858   0.01147  -0.1476   0.8667   0.3598
  -1.500   0.3714   0.01794   0.01165  -0.1514   0.8655   0.5290
  -1.250   0.3892   0.01814   0.01210  -0.1488   0.8589   0.5991
  -1.000   0.4216   0.01806   0.01197  -0.1496   0.8551   0.6249
  -0.750   0.4582   0.01783   0.01171  -0.1509   0.8527   0.6423
  -0.500   0.4813   0.01784   0.01168  -0.1499   0.8439   0.6552
  -0.250   0.5167   0.01746   0.01129  -0.1508   0.8403   0.6651
   0.000   0.5380   0.01748   0.01130  -0.1494   0.8306   0.6726
   0.250   0.5724   0.01712   0.01093  -0.1502   0.8268   0.6806
   0.500   0.5922   0.01717   0.01099  -0.1485   0.8154   0.6867
   0.750   0.6143   0.01713   0.01096  -0.1471   0.8041   0.6925
   1.000   0.6439   0.01691   0.01072  -0.1472   0.7934   0.6990
   1.250   0.6725   0.01658   0.01042  -0.1467   0.7838   0.7039
   1.500   0.7026   0.01641   0.01022  -0.1468   0.7708   0.7126
   1.750   0.7316   0.01610   0.00995  -0.1462   0.7579   0.7182
   2.000   0.7713   0.01559   0.00941  -0.1479   0.7434   0.7255
   2.250   0.8160   0.01494   0.00870  -0.1501   0.7243   0.7321
   2.500   0.8579   0.01460   0.00827  -0.1521   0.6978   0.7390
   2.750   0.8982   0.01451   0.00800  -0.1542   0.6650   0.7446
   3.000   0.9261   0.01469   0.00801  -0.1540   0.6268   0.7466
   3.250   0.9487   0.01506   0.00816  -0.1530   0.5854   0.7482
   3.500   0.9671   0.01555   0.00844  -0.1513   0.5451   0.7502
   3.750   0.9846   0.01608   0.00879  -0.1496   0.5077   0.7522
   4.000   1.0028   0.01662   0.00916  -0.1481   0.4736   0.7540
   4.250   1.0218   0.01718   0.00957  -0.1469   0.4418   0.7561
   4.500   1.0417   0.01775   0.00999  -0.1459   0.4121   0.7583
   4.750   1.0593   0.01830   0.01045  -0.1443   0.3854   0.7596
   5.000   1.0771   0.01887   0.01092  -0.1428   0.3612   0.7607
   5.250   1.0960   0.01940   0.01139  -0.1415   0.3395   0.7619
   5.500   1.1152   0.01995   0.01188  -0.1403   0.3210   0.7633
   5.750   1.1350   0.02048   0.01238  -0.1392   0.3053   0.7649
   6.000   1.1556   0.02100   0.01291  -0.1383   0.2914   0.7666
   6.250   1.1769   0.02153   0.01343  -0.1375   0.2790   0.7682
   6.500   1.1983   0.02207   0.01398  -0.1368   0.2681   0.7697
   6.750   1.2191   0.02267   0.01456  -0.1360   0.2579   0.7713
   7.000   1.2415   0.02320   0.01514  -0.1355   0.2483   0.7728
   7.250   1.2622   0.02379   0.01577  -0.1347   0.2408   0.7742
   7.500   1.2823   0.02433   0.01639  -0.1337   0.2338   0.7754
   7.750   1.3012   0.02494   0.01704  -0.1325   0.2252   0.7768
   8.000   1.3186   0.02564   0.01773  -0.1312   0.2123   0.7783
   8.250   1.3361   0.02636   0.01844  -0.1300   0.1993   0.7798
   8.500   1.3559   0.02697   0.01916  -0.1291   0.1895   0.7813
   8.750   1.3742   0.02768   0.01991  -0.1281   0.1772   0.7828
   9.000   1.3904   0.02855   0.02073  -0.1269   0.1588   0.7844
   9.250   1.4065   0.02951   0.02162  -0.1257   0.1337   0.7860
   9.500   1.4061   0.03201   0.02347  -0.1227   0.0581   0.7875
  10.000   1.4128   0.03646   0.02765  -0.1174   0.0099   0.7899
  10.250   1.4225   0.03799   0.02930  -0.1155   0.0079   0.7913
  10.500   1.4304   0.03971   0.03118  -0.1135   0.0065   0.7928
  10.750   1.4399   0.04127   0.03292  -0.1117   0.0060   0.7945
  11.000   1.4477   0.04303   0.03490  -0.1099   0.0057   0.7962
  11.250   1.4539   0.04499   0.03705  -0.1081   0.0054   0.7978
  11.500   1.4588   0.04713   0.03939  -0.1064   0.0052   0.7994
  11.750   1.4614   0.04955   0.04199  -0.1047   0.0050   0.8010
  12.000   1.4627   0.05221   0.04484  -0.1032   0.0048   0.8026
  12.250   1.4616   0.05521   0.04803  -0.1018   0.0046   0.8042
  12.500   1.4586   0.05846   0.05147  -0.1004   0.0045   0.8053
  12.750   1.4538   0.06209   0.05530  -0.0994   0.0044   0.8066
  13.000   1.4484   0.06600   0.05939  -0.0987   0.0043   0.8079
  13.250   1.4409   0.07039   0.06397  -0.0984   0.0043   0.8093
  13.500   1.4328   0.07511   0.06887  -0.0985   0.0042   0.8107
  13.750   1.4224   0.08041   0.07436  -0.0992   0.0041   0.8121
  14.000   1.4133   0.08577   0.07990  -0.1002   0.0041   0.8136
  14.250   1.4026   0.09157   0.08588  -0.1017   0.0040   0.8151
  14.500   1.3942   0.09724   0.09171  -0.1034   0.0040   0.8166
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