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EPPLER 68 AIRFOIL (e68-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 68 AIRFOIL (e68-il)
Reynolds number: 1,000,000
Max Cl/Cd: 114.06 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e68-il-1000000-n5.txt
Download as CSV file: xf-e68-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 68 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -16.000  -0.6250   0.11507   0.11303  -0.0509   1.0000   0.0058
 -15.750  -0.6838   0.09951   0.09729  -0.0582   1.0000   0.0057
 -15.500  -0.7220   0.08901   0.08666  -0.0632   1.0000   0.0057
 -15.250  -0.7622   0.07886   0.07640  -0.0682   1.0000   0.0056
 -15.000  -0.8021   0.06919   0.06659  -0.0730   1.0000   0.0056
 -14.750  -0.8399   0.06022   0.05747  -0.0774   1.0000   0.0055
 -14.500  -0.8681   0.05290   0.05003  -0.0810   1.0000   0.0055
 -14.250  -0.8787   0.04546   0.04241  -0.0885   0.9989   0.0055
 -14.000  -0.8800   0.03943   0.03621  -0.0957   0.9969   0.0056
 -13.750  -0.8724   0.03512   0.03176  -0.1016   0.9946   0.0056
 -13.500  -0.8671   0.03142   0.02792  -0.1060   0.9912   0.0057
 -13.250  -0.8563   0.02863   0.02499  -0.1096   0.9875   0.0057
 -13.000  -0.8399   0.02646   0.02269  -0.1128   0.9846   0.0058
 -12.750  -0.8290   0.02491   0.02104  -0.1134   0.9787   0.0059
 -12.500  -0.8124   0.02362   0.01964  -0.1141   0.9739   0.0060
 -12.250  -0.7892   0.02228   0.01819  -0.1157   0.9714   0.0061
 -12.000  -0.7743   0.02127   0.01707  -0.1150   0.9638   0.0062
 -11.750  -0.7473   0.02034   0.01605  -0.1165   0.9607   0.0064
 -11.500  -0.7209   0.01937   0.01497  -0.1178   0.9573   0.0065
 -11.250  -0.6985   0.01848   0.01398  -0.1180   0.9507   0.0067
 -11.000  -0.6713   0.01761   0.01300  -0.1191   0.9460   0.0068
 -10.750  -0.6467   0.01685   0.01214  -0.1195   0.9397   0.0069
 -10.500  -0.6207   0.01622   0.01141  -0.1200   0.9333   0.0071
 -10.250  -0.5960   0.01563   0.01072  -0.1201   0.9269   0.0072
 -10.000  -0.5721   0.01508   0.01008  -0.1199   0.9197   0.0073
  -9.750  -0.5480   0.01459   0.00950  -0.1198   0.9133   0.0074
  -9.500  -0.5249   0.01410   0.00893  -0.1194   0.9062   0.0074
  -9.250  -0.5035   0.01338   0.00808  -0.1188   0.8997   0.0077
  -9.000  -0.4807   0.01286   0.00749  -0.1182   0.8930   0.0079
  -8.750  -0.4565   0.01242   0.00696  -0.1179   0.8871   0.0082
  -8.500  -0.4323   0.01203   0.00652  -0.1175   0.8813   0.0084
  -8.250  -0.4076   0.01167   0.00610  -0.1172   0.8753   0.0087
  -8.000  -0.3824   0.01135   0.00571  -0.1169   0.8698   0.0090
  -7.750  -0.3571   0.01105   0.00536  -0.1166   0.8639   0.0093
  -7.500  -0.3315   0.01077   0.00500  -0.1164   0.8582   0.0096
  -7.250  -0.3057   0.01050   0.00469  -0.1162   0.8527   0.0100
  -7.000  -0.2796   0.01027   0.00441  -0.1160   0.8467   0.0103
  -6.750  -0.2539   0.00998   0.00406  -0.1157   0.8411   0.0113
  -6.500  -0.2277   0.00973   0.00378  -0.1155   0.8351   0.0121
  -6.250  -0.2014   0.00952   0.00352  -0.1153   0.8291   0.0131
  -6.000  -0.1749   0.00932   0.00329  -0.1152   0.8234   0.0148
  -5.750  -0.1487   0.00907   0.00304  -0.1150   0.8170   0.0197
  -5.500  -0.1226   0.00881   0.00280  -0.1148   0.8113   0.0303
  -5.250  -0.0959   0.00860   0.00261  -0.1147   0.8051   0.0394
  -5.000  -0.0694   0.00842   0.00243  -0.1146   0.7989   0.0485
  -4.750  -0.0426   0.00822   0.00227  -0.1145   0.7928   0.0609
  -4.500  -0.0161   0.00802   0.00211  -0.1144   0.7862   0.0781
  -4.250   0.0108   0.00785   0.00198  -0.1143   0.7800   0.0939
  -4.000   0.0377   0.00769   0.00185  -0.1142   0.7732   0.1117
  -3.750   0.0646   0.00754   0.00173  -0.1142   0.7669   0.1300
  -3.500   0.0916   0.00739   0.00163  -0.1141   0.7596   0.1509
  -3.250   0.1182   0.00722   0.00153  -0.1140   0.7530   0.1804
  -2.750   0.1723   0.00700   0.00138  -0.1139   0.7386   0.2232
  -2.500   0.1995   0.00686   0.00132  -0.1138   0.7313   0.2545
  -2.250   0.2264   0.00677   0.00127  -0.1137   0.7240   0.2787
  -2.000   0.2537   0.00667   0.00122  -0.1137   0.7165   0.3058
  -1.750   0.2806   0.00660   0.00119  -0.1136   0.7090   0.3326
  -1.500   0.3079   0.00652   0.00116  -0.1136   0.7012   0.3574
  -1.250   0.3349   0.00647   0.00114  -0.1135   0.6935   0.3838
  -1.000   0.3621   0.00641   0.00114  -0.1134   0.6853   0.4104
  -0.750   0.3891   0.00637   0.00114  -0.1133   0.6774   0.4358
  -0.500   0.4161   0.00635   0.00114  -0.1132   0.6687   0.4595
  -0.250   0.4432   0.00632   0.00116  -0.1131   0.6602   0.4836
   0.000   0.4698   0.00633   0.00118  -0.1129   0.6508   0.5061
   0.250   0.4967   0.00632   0.00121  -0.1127   0.6405   0.5280
   0.500   0.5234   0.00634   0.00124  -0.1125   0.6303   0.5489
   0.750   0.5498   0.00637   0.00128  -0.1123   0.6197   0.5693
   1.000   0.5762   0.00640   0.00133  -0.1120   0.6085   0.5898
   1.250   0.6027   0.00643   0.00139  -0.1118   0.5977   0.6112
   1.500   0.6288   0.00648   0.00145  -0.1115   0.5857   0.6320
   1.750   0.6546   0.00654   0.00153  -0.1111   0.5729   0.6532
   2.000   0.6802   0.00662   0.00161  -0.1107   0.5594   0.6744
   2.250   0.7057   0.00669   0.00170  -0.1103   0.5465   0.6950
   2.500   0.7311   0.00679   0.00181  -0.1098   0.5328   0.7149
   3.000   0.7810   0.00702   0.00203  -0.1088   0.5025   0.7511
   3.250   0.8054   0.00715   0.00215  -0.1081   0.4850   0.7681
   3.500   0.8295   0.00730   0.00229  -0.1074   0.4674   0.7853
   3.750   0.8531   0.00748   0.00244  -0.1066   0.4484   0.8016
   4.000   0.8760   0.00768   0.00260  -0.1057   0.4288   0.8177
   4.250   0.8986   0.00788   0.00277  -0.1047   0.4070   0.8337
   4.500   0.9201   0.00814   0.00298  -0.1035   0.3837   0.8497
   4.750   0.9413   0.00838   0.00318  -0.1023   0.3602   0.8662
   5.000   0.9616   0.00865   0.00339  -0.1009   0.3373   0.8834
   5.250   0.9804   0.00894   0.00362  -0.0991   0.3126   0.9024
   5.500   0.9976   0.00922   0.00386  -0.0970   0.2875   0.9251
   5.750   1.0150   0.00958   0.00413  -0.0951   0.2568   0.9617
   6.000   1.0369   0.01006   0.00445  -0.0943   0.2237   1.0000
   6.250   1.0535   0.01053   0.00476  -0.0924   0.1955   1.0000
   6.500   1.0713   0.01093   0.00507  -0.0907   0.1740   1.0000
   6.750   1.0879   0.01140   0.00542  -0.0887   0.1516   1.0000
   7.000   1.1042   0.01188   0.00579  -0.0868   0.1294   1.0000
   7.250   1.1200   0.01238   0.00618  -0.0848   0.1091   1.0000
   7.500   1.1373   0.01282   0.00656  -0.0831   0.0947   1.0000
   7.750   1.1533   0.01332   0.00698  -0.0813   0.0793   1.0000
   8.000   1.1692   0.01383   0.00742  -0.0794   0.0663   1.0000
   8.250   1.1859   0.01431   0.00785  -0.0777   0.0564   1.0000
   8.500   1.2017   0.01483   0.00833  -0.0759   0.0470   1.0000
   8.750   1.2169   0.01538   0.00884  -0.0740   0.0383   1.0000
   9.000   1.2321   0.01594   0.00938  -0.0722   0.0316   1.0000
   9.250   1.2467   0.01655   0.00995  -0.0703   0.0253   1.0000
   9.500   1.2609   0.01718   0.01056  -0.0685   0.0197   1.0000
   9.750   1.2744   0.01787   0.01123  -0.0665   0.0147   1.0000
  10.000   1.2885   0.01853   0.01190  -0.0647   0.0120   1.0000
  10.250   1.3027   0.01920   0.01259  -0.0630   0.0105   1.0000
  10.500   1.3173   0.01986   0.01329  -0.0614   0.0097   1.0000
  10.750   1.3305   0.02062   0.01407  -0.0597   0.0088   1.0000
  11.000   1.3433   0.02143   0.01491  -0.0580   0.0081   1.0000
  11.250   1.3570   0.02218   0.01571  -0.0565   0.0078   1.0000
  11.500   1.3701   0.02299   0.01656  -0.0549   0.0074   1.0000
  11.750   1.3828   0.02385   0.01747  -0.0534   0.0072   1.0000
  12.000   1.3945   0.02480   0.01847  -0.0518   0.0069   1.0000
  12.250   1.4058   0.02579   0.01952  -0.0503   0.0066   1.0000
  12.500   1.4160   0.02689   0.02066  -0.0488   0.0064   1.0000
  12.750   1.4253   0.02810   0.02192  -0.0472   0.0061   1.0000
  13.000   1.4325   0.02949   0.02339  -0.0455   0.0058   1.0000
  13.250   1.4416   0.03077   0.02472  -0.0442   0.0056   1.0000
  13.500   1.4512   0.03204   0.02605  -0.0429   0.0055   1.0000
  13.750   1.4603   0.03339   0.02746  -0.0418   0.0054   1.0000
  14.000   1.4682   0.03488   0.02902  -0.0406   0.0052   1.0000
  14.250   1.4753   0.03647   0.03068  -0.0395   0.0051   1.0000
  14.500   1.4820   0.03816   0.03245  -0.0385   0.0050   1.0000
  14.750   1.4881   0.03996   0.03433  -0.0376   0.0048   1.0000
  15.000   1.4935   0.04188   0.03632  -0.0367   0.0048   1.0000
  15.250   1.4975   0.04400   0.03852  -0.0360   0.0047   1.0000
  15.500   1.5022   0.04612   0.04071  -0.0354   0.0045   1.0000
  15.750   1.5048   0.04854   0.04321  -0.0349   0.0044   1.0000
  16.000   1.5078   0.05097   0.04572  -0.0345   0.0043   1.0000
  16.250   1.5092   0.05367   0.04850  -0.0343   0.0042   1.0000
  16.500   1.5092   0.05663   0.05154  -0.0342   0.0041   1.0000
  16.750   1.5067   0.06000   0.05502  -0.0343   0.0041   1.0000
  17.000   1.5031   0.06364   0.05876  -0.0346   0.0039   1.0000
  17.250   1.4987   0.06750   0.06274  -0.0352   0.0039   1.0000
  17.500   1.4912   0.07193   0.06729  -0.0361   0.0038   1.0000
  17.750   1.4870   0.07605   0.07151  -0.0371   0.0038   1.0000
  18.000   1.4842   0.08006   0.07563  -0.0383   0.0038   1.0000
  18.250   1.4806   0.08426   0.07993  -0.0396   0.0037   1.0000
  18.500   1.4734   0.08915   0.08494  -0.0413   0.0037   1.0000
  18.750   1.4665   0.09413   0.09003  -0.0432   0.0037   1.0000
  19.000   1.4576   0.09958   0.09560  -0.0454   0.0036   1.0000
  19.250   1.4487   0.10510   0.10124  -0.0478   0.0036   1.0000
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