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EPPLER 668 AIRFOIL (e668-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 668 AIRFOIL (e668-il)
Reynolds number: 100,000
Max Cl/Cd: 47.17 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e668-il-100000-n5.txt
Download as CSV file: xf-e668-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 668 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.1942   0.09818   0.09296  -0.0998   0.9449   0.0232
 -10.500  -0.1923   0.09285   0.08765  -0.1035   0.9426   0.0226
 -10.250  -0.2086   0.08376   0.07861  -0.1087   0.9380   0.0211
 -10.000  -0.2114   0.07782   0.07269  -0.1128   0.9345   0.0210
  -9.750  -0.2154   0.07043   0.06529  -0.1188   0.9312   0.0207
  -9.500  -0.2218   0.06326   0.05807  -0.1260   0.9274   0.0203
  -9.250  -0.2443   0.05841   0.05312  -0.1288   0.9206   0.0200
  -9.000  -0.2650   0.05398   0.04850  -0.1308   0.9149   0.0198
  -8.750  -0.2877   0.05185   0.04623  -0.1278   0.9081   0.0197
  -8.500  -0.3059   0.04890   0.04302  -0.1254   0.9024   0.0197
  -8.250  -0.3093   0.04539   0.03912  -0.1248   0.8989   0.0196
  -8.000  -0.3197   0.04343   0.03688  -0.1208   0.8933   0.0196
  -7.750  -0.3247   0.04124   0.03435  -0.1174   0.8885   0.0198
  -7.500  -0.3171   0.03825   0.03084  -0.1160   0.8853   0.0202
  -7.250  -0.2998   0.03550   0.02754  -0.1156   0.8831   0.0207
  -7.000  -0.2839   0.03355   0.02522  -0.1144   0.8807   0.0214
  -6.750  -0.2869   0.03315   0.02476  -0.1096   0.8750   0.0220
  -6.500  -0.2689   0.03215   0.02356  -0.1086   0.8719   0.0239
  -6.250  -0.2453   0.03078   0.02192  -0.1084   0.8698   0.0264
  -6.000  -0.2198   0.02967   0.02067  -0.1085   0.8681   0.0288
  -5.750  -0.1933   0.02845   0.01930  -0.1087   0.8667   0.0317
  -5.500  -0.1924   0.02832   0.01912  -0.1043   0.8609   0.0345
  -5.250  -0.1771   0.02773   0.01847  -0.1025   0.8572   0.0385
  -5.000  -0.1533   0.02701   0.01767  -0.1022   0.8548   0.0452
  -4.750  -0.1253   0.02625   0.01689  -0.1027   0.8530   0.0547
  -4.500  -0.0950   0.02553   0.01615  -0.1036   0.8515   0.0691
  -4.250  -0.0640   0.02481   0.01548  -0.1046   0.8502   0.0922
  -4.000  -0.0707   0.02503   0.01576  -0.0990   0.8421   0.1050
  -3.750  -0.0451   0.02451   0.01542  -0.0991   0.8394   0.1487
  -3.500  -0.0162   0.02393   0.01511  -0.0999   0.8375   0.2188
  -3.250   0.0146   0.02332   0.01487  -0.1010   0.8360   0.3151
  -3.000   0.0460   0.02270   0.01469  -0.1021   0.8347   0.4334
  -2.750   0.0409   0.02300   0.01528  -0.0966   0.8262   0.4968
  -2.500   0.0610   0.02285   0.01555  -0.0946   0.8232   0.6089
  -2.250   0.0827   0.02299   0.01587  -0.0922   0.8210   0.6893
  -2.000   0.1108   0.02319   0.01600  -0.0914   0.8194   0.7411
  -1.750   0.1067   0.02388   0.01666  -0.0859   0.8103   0.7675
  -1.500   0.1305   0.02409   0.01675  -0.0846   0.8071   0.7967
  -1.250   0.1564   0.02419   0.01674  -0.0835   0.8050   0.8199
  -1.000   0.1607   0.02467   0.01718  -0.0793   0.7976   0.8386
  -0.750   0.1777   0.02484   0.01726  -0.0770   0.7929   0.8569
  -0.500   0.2012   0.02481   0.01715  -0.0755   0.7902   0.8737
  -0.250   0.2283   0.02468   0.01693  -0.0746   0.7883   0.8899
   0.000   0.2253   0.02517   0.01741  -0.0695   0.7782   0.9063
   0.250   0.2513   0.02505   0.01722  -0.0687   0.7752   0.9222
   0.500   0.2844   0.02489   0.01698  -0.0692   0.7732   0.9373
   1.000   0.3401   0.02534   0.01736  -0.0705   0.7612   0.9672
   1.250   0.3859   0.02525   0.01721  -0.0741   0.7592   0.9770
   1.500   0.4313   0.02508   0.01697  -0.0775   0.7575   0.9857
   1.750   0.4377   0.02555   0.01744  -0.0751   0.7465   1.0000
   2.000   0.4704   0.02534   0.01718  -0.0760   0.7438   1.0000
   2.500   0.5123   0.02559   0.01739  -0.0748   0.7302   1.0000
   2.750   0.5476   0.02531   0.01709  -0.0761   0.7276   1.0000
   3.000   0.5602   0.02579   0.01757  -0.0745   0.7168   1.0000
   3.250   0.5966   0.02544   0.01723  -0.0758   0.7142   1.0000
   3.500   0.6111   0.02593   0.01773  -0.0745   0.7033   1.0000
   3.750   0.6468   0.02553   0.01734  -0.0757   0.7002   1.0000
   4.250   0.6986   0.02549   0.01738  -0.0756   0.6859   1.0000
   4.500   0.7176   0.02581   0.01774  -0.0747   0.6755   1.0000
   4.750   0.7514   0.02530   0.01727  -0.0754   0.6711   1.0000
   5.000   0.7715   0.02555   0.01759  -0.0746   0.6605   1.0000
   5.250   0.8062   0.02495   0.01703  -0.0753   0.6556   1.0000
   5.750   0.8559   0.02488   0.01710  -0.0746   0.6353   1.0000
   6.000   0.8853   0.02455   0.01684  -0.0746   0.6255   1.0000
   6.250   0.9096   0.02455   0.01691  -0.0741   0.6125   1.0000
   6.500   0.9374   0.02436   0.01679  -0.0740   0.5996   1.0000
   6.750   0.9678   0.02402   0.01651  -0.0741   0.5858   1.0000
   7.000   0.9988   0.02368   0.01621  -0.0742   0.5703   1.0000
   7.250   1.0295   0.02339   0.01594  -0.0743   0.5518   1.0000
   7.750   1.0845   0.02331   0.01584  -0.0738   0.5072   1.0000
   8.000   1.1089   0.02351   0.01598  -0.0732   0.4817   1.0000
   8.250   1.1280   0.02399   0.01640  -0.0721   0.4556   1.0000
   8.500   1.1442   0.02464   0.01700  -0.0707   0.4288   1.0000
   8.750   1.1586   0.02540   0.01769  -0.0692   0.4022   1.0000
   9.000   1.1708   0.02630   0.01851  -0.0674   0.3757   1.0000
   9.250   1.1817   0.02731   0.01947  -0.0657   0.3499   1.0000
   9.500   1.1915   0.02840   0.02049  -0.0638   0.3251   1.0000
   9.750   1.2005   0.02959   0.02162  -0.0620   0.3003   1.0000
  10.000   1.2087   0.03086   0.02285  -0.0602   0.2768   1.0000
  10.250   1.2160   0.03222   0.02416  -0.0585   0.2537   1.0000
  10.500   1.2231   0.03366   0.02555  -0.0567   0.2320   1.0000
  10.750   1.2297   0.03517   0.02702  -0.0551   0.2107   1.0000
  11.000   1.2353   0.03680   0.02861  -0.0535   0.1914   1.0000
  11.250   1.2413   0.03847   0.03027  -0.0520   0.1729   1.0000
  11.500   1.2469   0.04021   0.03201  -0.0505   0.1557   1.0000
  11.750   1.2521   0.04205   0.03385  -0.0492   0.1402   1.0000
  12.000   1.2567   0.04399   0.03580  -0.0479   0.1262   1.0000
  12.250   1.2610   0.04602   0.03785  -0.0467   0.1141   1.0000
  12.500   1.2643   0.04820   0.04005  -0.0455   0.1032   1.0000
  12.750   1.2669   0.05054   0.04242  -0.0445   0.0937   1.0000
  13.000   1.2710   0.05279   0.04477  -0.0436   0.0846   1.0000
  13.250   1.2731   0.05531   0.04735  -0.0428   0.0774   1.0000
  13.500   1.2742   0.05801   0.05011  -0.0421   0.0709   1.0000
  13.750   1.2765   0.06068   0.05289  -0.0415   0.0650   1.0000
  14.000   1.2763   0.06368   0.05597  -0.0411   0.0603   1.0000
  14.250   1.2774   0.06664   0.05905  -0.0408   0.0558   1.0000
  14.500   1.2777   0.06977   0.06230  -0.0407   0.0520   1.0000
  14.750   1.2758   0.07322   0.06581  -0.0407   0.0489   1.0000
  15.000   1.2770   0.07641   0.06920  -0.0407   0.0455   1.0000
  15.250   1.2756   0.07998   0.07287  -0.0411   0.0429   1.0000
  15.500   1.2740   0.08365   0.07663  -0.0415   0.0407   1.0000
  15.750   1.2741   0.08721   0.08040  -0.0420   0.0382   1.0000
  16.000   1.2721   0.09111   0.08441  -0.0429   0.0361   1.0000
  16.250   1.2691   0.09513   0.08848  -0.0439   0.0346   1.0000
  16.500   1.2681   0.09911   0.09271  -0.0449   0.0327   1.0000
  16.750   1.2655   0.10334   0.09714  -0.0462   0.0310   1.0000
  17.000   1.2620   0.10775   0.10166  -0.0479   0.0296   1.0000
  17.250   1.2593   0.11196   0.10589  -0.0495   0.0285   1.0000
  17.500   1.2538   0.11705   0.11127  -0.0516   0.0272   1.0000
  17.750   1.2481   0.12219   0.11664  -0.0539   0.0260   1.0000
  18.000   1.2425   0.12736   0.12196  -0.0566   0.0250   1.0000
  18.250   1.2382   0.13228   0.12698  -0.0593   0.0241   1.0000
  18.500   1.2346   0.13704   0.13178  -0.0619   0.0233   1.0000
  18.750   1.2235   0.14388   0.13890  -0.0659   0.0227   1.0000
  19.000   1.2116   0.15105   0.14632  -0.0704   0.0222   1.0000
  19.250   1.1985   0.15876   0.15424  -0.0753   0.0218   1.0000
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