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EPPLER 68 AIRFOIL (e68-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 68 AIRFOIL (e68-il)
Reynolds number: 500,000
Max Cl/Cd: 114.89 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e68-il-500000.txt
Download as CSV file: xf-e68-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.3938   0.11774   0.11547  -0.0435   1.0000   0.0267
 -11.500  -0.4996   0.08585   0.08363  -0.0546   1.0000   0.0181
 -11.250  -0.6656   0.04506   0.04199  -0.0913   0.9930   0.0145
 -11.000  -0.6678   0.04025   0.03690  -0.0977   0.9864   0.0145
 -10.750  -0.6665   0.03630   0.03261  -0.1006   0.9793   0.0145
 -10.500  -0.6536   0.03281   0.02880  -0.1031   0.9742   0.0145
 -10.250  -0.6287   0.03090   0.02676  -0.1057   0.9722   0.0151
 -10.000  -0.6166   0.02853   0.02413  -0.1054   0.9657   0.0151
  -9.750  -0.5944   0.02620   0.02154  -0.1066   0.9623   0.0153
  -9.500  -0.5673   0.02412   0.01922  -0.1083   0.9603   0.0155
  -9.250  -0.5371   0.02239   0.01728  -0.1102   0.9590   0.0158
  -9.000  -0.5172   0.02116   0.01591  -0.1096   0.9535   0.0161
  -8.750  -0.4893   0.01989   0.01448  -0.1105   0.9505   0.0165
  -8.500  -0.4579   0.01869   0.01315  -0.1120   0.9487   0.0169
  -8.250  -0.4260   0.01760   0.01194  -0.1135   0.9470   0.0174
  -8.000  -0.3932   0.01666   0.01089  -0.1151   0.9455   0.0178
  -7.750  -0.3694   0.01602   0.01016  -0.1146   0.9403   0.0182
  -7.500  -0.3457   0.01474   0.00878  -0.1146   0.9358   0.0192
  -7.250  -0.3145   0.01403   0.00803  -0.1158   0.9331   0.0207
  -7.000  -0.2822   0.01340   0.00734  -0.1170   0.9308   0.0221
  -6.750  -0.2599   0.01298   0.00684  -0.1160   0.9243   0.0234
  -6.500  -0.2322   0.01224   0.00605  -0.1163   0.9200   0.0265
  -6.250  -0.2017   0.01165   0.00543  -0.1171   0.9167   0.0336
  -6.000  -0.1790   0.01110   0.00499  -0.1163   0.9103   0.0553
  -5.750  -0.1510   0.01073   0.00466  -0.1166   0.9055   0.0744
  -5.500  -0.1209   0.01036   0.00433  -0.1173   0.9017   0.0940
  -5.250  -0.0967   0.01011   0.00412  -0.1167   0.8952   0.1123
  -5.000  -0.0689   0.00980   0.00387  -0.1168   0.8901   0.1346
  -4.750  -0.0402   0.00951   0.00364  -0.1172   0.8856   0.1624
  -4.500  -0.0155   0.00925   0.00347  -0.1167   0.8791   0.1935
  -4.250   0.0125   0.00897   0.00328  -0.1169   0.8741   0.2298
  -4.000   0.0391   0.00872   0.00313  -0.1168   0.8685   0.2646
  -3.750   0.0655   0.00850   0.00299  -0.1167   0.8624   0.3002
  -3.500   0.0945   0.00830   0.00284  -0.1170   0.8576   0.3357
  -3.250   0.1198   0.00811   0.00276  -0.1166   0.8510   0.3712
  -3.000   0.1474   0.00794   0.00266  -0.1166   0.8453   0.4108
  -2.750   0.1748   0.00780   0.00258  -0.1165   0.8396   0.4454
  -2.500   0.2014   0.00767   0.00252  -0.1163   0.8329   0.4770
  -2.250   0.2304   0.00758   0.00245  -0.1165   0.8277   0.5072
  -1.750   0.2842   0.00741   0.00237  -0.1161   0.8146   0.5610
  -1.500   0.3108   0.00735   0.00235  -0.1158   0.8077   0.5862
  -1.250   0.3382   0.00729   0.00232  -0.1157   0.8011   0.6113
  -1.000   0.3653   0.00725   0.00232  -0.1155   0.7945   0.6354
  -0.750   0.3922   0.00721   0.00231  -0.1152   0.7874   0.6592
  -0.500   0.4195   0.00718   0.00232  -0.1150   0.7807   0.6822
  -0.250   0.4461   0.00716   0.00233  -0.1147   0.7732   0.7042
   0.000   0.4731   0.00716   0.00236  -0.1144   0.7662   0.7252
   0.250   0.4994   0.00715   0.00238  -0.1140   0.7583   0.7460
   0.500   0.5261   0.00717   0.00242  -0.1137   0.7509   0.7654
   0.750   0.5520   0.00717   0.00245  -0.1131   0.7426   0.7840
   1.000   0.5777   0.00719   0.00251  -0.1126   0.7343   0.8024
   1.250   0.6036   0.00723   0.00254  -0.1120   0.7259   0.8203
   1.500   0.6283   0.00725   0.00260  -0.1113   0.7166   0.8378
   1.750   0.6535   0.00730   0.00266  -0.1106   0.7080   0.8548
   2.000   0.6774   0.00733   0.00272  -0.1096   0.6984   0.8710
   2.250   0.7006   0.00737   0.00278  -0.1085   0.6886   0.8873
   2.500   0.7232   0.00742   0.00284  -0.1072   0.6789   0.9037
   2.750   0.7444   0.00746   0.00289  -0.1056   0.6683   0.9213
   3.000   0.7653   0.00748   0.00293  -0.1039   0.6577   0.9408
   3.250   0.7908   0.00753   0.00298  -0.1033   0.6472   0.9611
   3.500   0.8254   0.00762   0.00305  -0.1048   0.6352   0.9792
   3.750   0.8625   0.00773   0.00312  -0.1070   0.6219   1.0000
   4.000   0.8858   0.00785   0.00321  -0.1063   0.6085   1.0000
   4.250   0.9098   0.00799   0.00333  -0.1056   0.5948   1.0000
   4.500   0.9337   0.00815   0.00345  -0.1050   0.5806   1.0000
   4.750   0.9570   0.00833   0.00359  -0.1042   0.5652   1.0000
   5.000   0.9799   0.00853   0.00374  -0.1033   0.5490   1.0000
   5.250   1.0022   0.00874   0.00391  -0.1023   0.5317   1.0000
   5.500   1.0243   0.00896   0.00410  -0.1012   0.5135   1.0000
   5.750   1.0455   0.00922   0.00430  -0.1000   0.4938   1.0000
   6.000   1.0651   0.00952   0.00452  -0.0985   0.4718   1.0000
   6.250   1.0836   0.00986   0.00478  -0.0969   0.4464   1.0000
   6.500   1.1015   0.01023   0.00506  -0.0951   0.4203   1.0000
   6.750   1.1160   0.01066   0.00537  -0.0926   0.3902   1.0000
   7.000   1.1294   0.01114   0.00572  -0.0901   0.3593   1.0000
   7.250   1.1422   0.01170   0.00612  -0.0875   0.3273   1.0000
   7.500   1.1546   0.01230   0.00658  -0.0849   0.2947   1.0000
   7.750   1.1661   0.01299   0.00709  -0.0822   0.2594   1.0000
   8.000   1.1776   0.01370   0.00764  -0.0796   0.2274   1.0000
   8.500   1.2005   0.01520   0.00884  -0.0747   0.1696   1.0000
   8.750   1.2132   0.01591   0.00945  -0.0725   0.1480   1.0000
   9.000   1.2248   0.01670   0.01015  -0.0702   0.1273   1.0000
   9.250   1.2369   0.01747   0.01084  -0.0681   0.1098   1.0000
   9.500   1.2487   0.01827   0.01158  -0.0659   0.0934   1.0000
   9.750   1.2597   0.01914   0.01238  -0.0638   0.0786   1.0000
  10.000   1.2698   0.02009   0.01326  -0.0616   0.0648   1.0000
  10.250   1.2789   0.02113   0.01423  -0.0594   0.0514   1.0000
  10.500   1.2870   0.02226   0.01531  -0.0571   0.0385   1.0000
  10.750   1.2914   0.02370   0.01668  -0.0545   0.0273   1.0000
  11.000   1.2988   0.02497   0.01798  -0.0524   0.0227   1.0000
  11.250   1.3043   0.02642   0.01945  -0.0501   0.0199   1.0000
  11.500   1.3121   0.02774   0.02086  -0.0482   0.0185   1.0000
  11.750   1.3204   0.02906   0.02225  -0.0465   0.0175   1.0000
  12.000   1.3279   0.03047   0.02372  -0.0449   0.0164   1.0000
  12.250   1.3324   0.03217   0.02547  -0.0432   0.0155   1.0000
  12.500   1.3298   0.03452   0.02793  -0.0411   0.0147   1.0000
  12.750   1.3359   0.03622   0.02972  -0.0397   0.0143   1.0000
  13.000   1.3414   0.03802   0.03163  -0.0385   0.0138   1.0000
  13.250   1.3453   0.04004   0.03375  -0.0373   0.0134   1.0000
  13.500   1.3481   0.04223   0.03604  -0.0362   0.0131   1.0000
  13.750   1.3512   0.04447   0.03837  -0.0353   0.0127   1.0000
  14.000   1.3522   0.04700   0.04099  -0.0345   0.0124   1.0000
  14.250   1.3538   0.04957   0.04364  -0.0339   0.0121   1.0000
  14.500   1.3532   0.05245   0.04661  -0.0334   0.0118   1.0000
  14.750   1.3501   0.05571   0.04996  -0.0331   0.0115   1.0000
  15.000   1.3453   0.05929   0.05364  -0.0328   0.0112   1.0000
  15.250   1.3389   0.06318   0.05764  -0.0325   0.0110   1.0000
  15.500   1.3426   0.06595   0.06055  -0.0329   0.0108   1.0000
  15.750   1.3432   0.06919   0.06390  -0.0332   0.0106   1.0000
  16.000   1.3446   0.07242   0.06727  -0.0337   0.0103   1.0000
  16.250   1.3437   0.07602   0.07099  -0.0344   0.0101   1.0000
  16.500   1.3421   0.07979   0.07488  -0.0352   0.0100   1.0000
  16.750   1.3392   0.08381   0.07903  -0.0360   0.0099   1.0000
  17.000   1.3369   0.08789   0.08323  -0.0373   0.0096   1.0000
  17.250   1.3335   0.09219   0.08766  -0.0386   0.0095   1.0000
  17.500   1.3295   0.09670   0.09230  -0.0402   0.0094   1.0000
  17.750   1.3246   0.10141   0.09714  -0.0420   0.0093   1.0000
  18.000   1.3198   0.10624   0.10209  -0.0440   0.0092   1.0000
  18.250   1.3142   0.11128   0.10725  -0.0463   0.0090   1.0000
  18.500   1.3081   0.11650   0.11260  -0.0487   0.0089   1.0000
  18.750   1.3016   0.12184   0.11807  -0.0514   0.0089   1.0000
  19.000   1.2942   0.12745   0.12381  -0.0544   0.0088   1.0000
  19.250   1.2863   0.13326   0.12975  -0.0576   0.0087   1.0000
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