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EPPLER 68 AIRFOIL (e68-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 68 AIRFOIL (e68-il)
Reynolds number: 1,000,000
Max Cl/Cd: 136.57 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e68-il-1000000.txt
Download as CSV file: xf-e68-il-1000000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.6005   0.08552   0.08366  -0.0602   1.0000   0.0095
 -13.250  -0.6595   0.07112   0.06910  -0.0677   1.0000   0.0092
 -13.000  -0.7031   0.06102   0.05885  -0.0728   1.0000   0.0090
 -12.750  -0.7266   0.05235   0.05001  -0.0802   0.9992   0.0090
 -12.500  -0.7304   0.04475   0.04220  -0.0902   0.9969   0.0090
 -12.250  -0.7313   0.03794   0.03512  -0.1001   0.9942   0.0090
 -12.000  -0.7320   0.03297   0.02988  -0.1061   0.9889   0.0090
 -11.750  -0.7182   0.03006   0.02678  -0.1104   0.9854   0.0090
 -11.500  -0.7085   0.02757   0.02407  -0.1120   0.9800   0.0091
 -11.250  -0.6914   0.02523   0.02152  -0.1135   0.9756   0.0092
 -11.000  -0.6673   0.02349   0.01961  -0.1154   0.9735   0.0093
 -10.750  -0.6409   0.02178   0.01773  -0.1174   0.9721   0.0094
 -10.500  -0.6207   0.02053   0.01633  -0.1174   0.9674   0.0096
 -10.250  -0.5943   0.01965   0.01534  -0.1183   0.9640   0.0099
 -10.000  -0.5662   0.01868   0.01426  -0.1194   0.9613   0.0101
  -9.750  -0.5361   0.01787   0.01334  -0.1208   0.9591   0.0103
  -9.500  -0.5175   0.01655   0.01188  -0.1201   0.9524   0.0105
  -9.250  -0.4963   0.01497   0.01015  -0.1201   0.9471   0.0109
  -9.000  -0.4715   0.01410   0.00918  -0.1203   0.9421   0.0112
  -8.750  -0.4484   0.01347   0.00848  -0.1199   0.9357   0.0115
  -8.500  -0.4208   0.01289   0.00782  -0.1203   0.9311   0.0119
  -8.250  -0.3979   0.01240   0.00727  -0.1197   0.9246   0.0122
  -8.000  -0.3722   0.01193   0.00672  -0.1196   0.9189   0.0125
  -7.750  -0.3467   0.01151   0.00621  -0.1194   0.9135   0.0129
  -7.500  -0.3223   0.01112   0.00576  -0.1190   0.9072   0.0133
  -7.250  -0.2954   0.01077   0.00533  -0.1190   0.9020   0.0137
  -7.000  -0.2714   0.01033   0.00481  -0.1184   0.8960   0.0144
  -6.750  -0.2460   0.00993   0.00436  -0.1181   0.8902   0.0158
  -6.500  -0.2194   0.00966   0.00403  -0.1180   0.8850   0.0171
  -6.250  -0.1938   0.00938   0.00371  -0.1176   0.8791   0.0190
  -6.000  -0.1677   0.00901   0.00336  -0.1174   0.8736   0.0272
  -5.750  -0.1424   0.00862   0.00307  -0.1172   0.8680   0.0481
  -5.500  -0.1161   0.00838   0.00286  -0.1170   0.8622   0.0622
  -5.250  -0.0890   0.00816   0.00266  -0.1170   0.8570   0.0772
  -5.000  -0.0628   0.00794   0.00250  -0.1168   0.8511   0.0935
  -4.750  -0.0359   0.00774   0.00233  -0.1167   0.8454   0.1129
  -4.500  -0.0092   0.00752   0.00218  -0.1167   0.8398   0.1373
  -4.250   0.0175   0.00732   0.00205  -0.1166   0.8337   0.1607
  -4.000   0.0447   0.00714   0.00192  -0.1166   0.8281   0.1879
  -3.750   0.0715   0.00696   0.00181  -0.1165   0.8220   0.2158
  -3.500   0.0985   0.00679   0.00171  -0.1164   0.8157   0.2460
  -3.250   0.1254   0.00659   0.00162  -0.1164   0.8097   0.2843
  -3.000   0.1525   0.00644   0.00154  -0.1163   0.8031   0.3149
  -2.750   0.1797   0.00632   0.00147  -0.1163   0.7970   0.3473
  -2.500   0.2068   0.00617   0.00142  -0.1162   0.7903   0.3843
  -2.250   0.2341   0.00609   0.00137  -0.1162   0.7839   0.4147
  -2.000   0.2615   0.00599   0.00134  -0.1161   0.7770   0.4442
  -1.750   0.2888   0.00593   0.00131  -0.1160   0.7703   0.4720
  -1.500   0.3163   0.00586   0.00130  -0.1160   0.7634   0.4970
  -1.250   0.3436   0.00582   0.00128  -0.1159   0.7563   0.5217
  -1.000   0.3710   0.00577   0.00128  -0.1159   0.7492   0.5461
  -0.750   0.3982   0.00574   0.00128  -0.1157   0.7418   0.5693
  -0.500   0.4256   0.00571   0.00129  -0.1157   0.7344   0.5924
  -0.250   0.4526   0.00570   0.00130  -0.1155   0.7266   0.6150
   0.000   0.4799   0.00568   0.00132  -0.1154   0.7185   0.6378
   0.250   0.5065   0.00570   0.00135  -0.1151   0.7101   0.6595
   0.500   0.5336   0.00568   0.00138  -0.1150   0.7012   0.6812
   0.750   0.5603   0.00571   0.00142  -0.1147   0.6926   0.7020
   1.000   0.5869   0.00572   0.00147  -0.1145   0.6832   0.7216
   1.250   0.6135   0.00574   0.00152  -0.1142   0.6740   0.7412
   1.500   0.6396   0.00579   0.00158  -0.1138   0.6642   0.7598
   1.750   0.6658   0.00584   0.00164  -0.1134   0.6536   0.7776
   2.000   0.6918   0.00589   0.00171  -0.1131   0.6429   0.7949
   2.250   0.7174   0.00595   0.00178  -0.1126   0.6326   0.8114
   2.500   0.7425   0.00603   0.00187  -0.1120   0.6214   0.8274
   2.750   0.7678   0.00610   0.00195  -0.1114   0.6096   0.8430
   3.000   0.7926   0.00618   0.00205  -0.1107   0.5971   0.8583
   3.250   0.8167   0.00627   0.00214  -0.1099   0.5839   0.8735
   3.500   0.8402   0.00637   0.00225  -0.1090   0.5707   0.8891
   3.750   0.8629   0.00648   0.00236  -0.1079   0.5566   0.9049
   4.000   0.8845   0.00659   0.00246  -0.1065   0.5420   0.9221
   4.250   0.9047   0.00670   0.00257  -0.1049   0.5262   0.9423
   4.500   0.9277   0.00682   0.00268  -0.1039   0.5089   0.9685
   4.750   0.9601   0.00703   0.00282  -0.1051   0.4892   1.0000
   5.000   0.9840   0.00725   0.00297  -0.1045   0.4702   1.0000
   5.250   1.0071   0.00750   0.00315  -0.1037   0.4488   1.0000
   5.500   1.0288   0.00780   0.00335  -0.1026   0.4235   1.0000
   5.750   1.0493   0.00816   0.00357  -0.1014   0.3942   1.0000
   6.000   1.0680   0.00860   0.00384  -0.0998   0.3589   1.0000
   6.250   1.0865   0.00904   0.00413  -0.0982   0.3272   1.0000
   6.500   1.1041   0.00946   0.00443  -0.0964   0.2979   1.0000
   6.750   1.1194   0.00996   0.00476  -0.0942   0.2647   1.0000
   7.000   1.1339   0.01050   0.00513  -0.0919   0.2317   1.0000
   7.250   1.1493   0.01101   0.00550  -0.0898   0.2046   1.0000
   7.500   1.1642   0.01154   0.00591  -0.0876   0.1790   1.0000
   7.750   1.1783   0.01211   0.00634  -0.0853   0.1534   1.0000
   8.000   1.1938   0.01263   0.00676  -0.0833   0.1328   1.0000
   8.250   1.2081   0.01320   0.00723  -0.0812   0.1138   1.0000
   8.500   1.2229   0.01376   0.00771  -0.0791   0.0967   1.0000
   8.750   1.2370   0.01436   0.00822  -0.0770   0.0812   1.0000
   9.000   1.2512   0.01496   0.00876  -0.0750   0.0682   1.0000
   9.250   1.2651   0.01557   0.00933  -0.0730   0.0570   1.0000
   9.500   1.2785   0.01623   0.00993  -0.0709   0.0467   1.0000
   9.750   1.2905   0.01698   0.01062  -0.0687   0.0363   1.0000
  10.000   1.3000   0.01788   0.01145  -0.0662   0.0251   1.0000
  10.250   1.3097   0.01881   0.01233  -0.0639   0.0174   1.0000
  10.500   1.3206   0.01968   0.01322  -0.0617   0.0144   1.0000
  10.750   1.3335   0.02046   0.01404  -0.0599   0.0131   1.0000
  11.000   1.3448   0.02136   0.01496  -0.0580   0.0119   1.0000
  11.250   1.3540   0.02242   0.01608  -0.0558   0.0110   1.0000
  11.500   1.3665   0.02328   0.01700  -0.0542   0.0106   1.0000
  11.750   1.3781   0.02423   0.01801  -0.0526   0.0103   1.0000
  12.000   1.3888   0.02526   0.01909  -0.0509   0.0098   1.0000
  12.250   1.3988   0.02637   0.02026  -0.0493   0.0095   1.0000
  12.500   1.4079   0.02757   0.02152  -0.0477   0.0092   1.0000
  12.750   1.4149   0.02897   0.02298  -0.0459   0.0088   1.0000
  13.000   1.4166   0.03083   0.02493  -0.0439   0.0084   1.0000
  13.250   1.4178   0.03281   0.02701  -0.0420   0.0080   1.0000
  13.500   1.4257   0.03429   0.02856  -0.0408   0.0079   1.0000
  13.750   1.4332   0.03583   0.03018  -0.0396   0.0077   1.0000
  14.000   1.4379   0.03770   0.03213  -0.0384   0.0076   1.0000
  14.250   1.4431   0.03959   0.03410  -0.0374   0.0074   1.0000
  14.500   1.4466   0.04170   0.03630  -0.0365   0.0072   1.0000
  14.750   1.4497   0.04392   0.03861  -0.0356   0.0070   1.0000
  15.000   1.4527   0.04623   0.04100  -0.0350   0.0069   1.0000
  15.250   1.4530   0.04892   0.04379  -0.0344   0.0068   1.0000
  15.500   1.4556   0.05145   0.04638  -0.0341   0.0066   1.0000
  15.750   1.4543   0.05451   0.04955  -0.0339   0.0065   1.0000
  16.000   1.4541   0.05754   0.05265  -0.0339   0.0063   1.0000
  16.250   1.4504   0.06115   0.05635  -0.0341   0.0062   1.0000
  16.500   1.4445   0.06515   0.06047  -0.0345   0.0061   1.0000
  16.750   1.4362   0.06964   0.06507  -0.0352   0.0061   1.0000
  17.000   1.4204   0.07535   0.07093  -0.0365   0.0058   1.0000
  17.250   1.4115   0.08030   0.07600  -0.0378   0.0058   1.0000
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