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EPPLER 584 AIRFOIL (e584-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 584 AIRFOIL (e584-il)
Reynolds number: 200,000
Max Cl/Cd: 64.44 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e584-il-200000-n5.txt
Download as CSV file: xf-e584-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 584 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.0783   0.08513   0.08053  -0.1194   0.7885   0.0133
 -10.750  -0.0743   0.08245   0.07780  -0.1204   0.7800   0.0131
 -10.500  -0.0749   0.07874   0.07408  -0.1220   0.7731   0.0129
 -10.250  -0.0769   0.07486   0.07019  -0.1238   0.7665   0.0127
  -9.750  -0.1009   0.06257   0.05790  -0.1315   0.7557   0.0121
  -9.250  -0.2061   0.04357   0.03823  -0.1314   0.7453   0.0106
  -9.000  -0.2242   0.04105   0.03550  -0.1272   0.7406   0.0106
  -8.750  -0.2352   0.03870   0.03293  -0.1234   0.7361   0.0105
  -8.500  -0.2404   0.03624   0.03016  -0.1200   0.7320   0.0105
  -8.250  -0.2403   0.03390   0.02748  -0.1170   0.7286   0.0104
  -8.000  -0.2360   0.03165   0.02491  -0.1143   0.7251   0.0104
  -7.750  -0.2290   0.02930   0.02215  -0.1117   0.7217   0.0104
  -7.500  -0.2166   0.02735   0.01985  -0.1097   0.7186   0.0104
  -7.250  -0.2001   0.02570   0.01785  -0.1081   0.7159   0.0105
  -7.000  -0.1809   0.02416   0.01597  -0.1069   0.7135   0.0106
  -6.750  -0.1600   0.02298   0.01461  -0.1061   0.7112   0.0108
  -6.500  -0.1385   0.02201   0.01352  -0.1052   0.7085   0.0110
  -6.250  -0.1165   0.02117   0.01258  -0.1045   0.7055   0.0114
  -6.000  -0.0939   0.02038   0.01166  -0.1037   0.7027   0.0118
  -5.750  -0.0713   0.01963   0.01080  -0.1030   0.7001   0.0123
  -5.500  -0.0486   0.01896   0.00998  -0.1022   0.6979   0.0130
  -5.250  -0.0264   0.01836   0.00931  -0.1014   0.6959   0.0138
  -5.000  -0.0041   0.01795   0.00886  -0.1006   0.6935   0.0152
  -4.750   0.0183   0.01754   0.00842  -0.0999   0.6910   0.0175
  -4.500   0.0408   0.01713   0.00795  -0.0990   0.6885   0.0199
  -4.250   0.0633   0.01670   0.00747  -0.0982   0.6860   0.0230
  -4.000   0.0863   0.01630   0.00704  -0.0975   0.6838   0.0290
  -3.750   0.1095   0.01591   0.00667  -0.0969   0.6820   0.0428
  -3.500   0.1310   0.01553   0.00643  -0.0960   0.6796   0.0687
  -3.000   0.1721   0.01467   0.00605  -0.0941   0.6744   0.1826
  -2.750   0.1902   0.01404   0.00586  -0.0929   0.6721   0.2970
  -2.500   0.2040   0.01316   0.00566  -0.0909   0.6699   0.4763
  -2.250   0.2187   0.01330   0.00685  -0.0860   0.6679   0.7200
  -2.000   0.2407   0.01369   0.00717  -0.0844   0.6656   0.7836
  -1.750   0.2620   0.01395   0.00733  -0.0831   0.6628   0.8088
  -1.500   0.2850   0.01428   0.00756  -0.0818   0.6602   0.8246
  -1.250   0.3094   0.01461   0.00781  -0.0806   0.6577   0.8363
  -1.000   0.3341   0.01506   0.00817  -0.0791   0.6555   0.8502
  -0.750   0.3593   0.01563   0.00865  -0.0774   0.6534   0.8692
  -0.500   0.3889   0.01598   0.00896  -0.0769   0.6510   0.8804
  -0.250   0.4039   0.01601   0.00896  -0.0746   0.6479   0.8875
   0.000   0.4306   0.01604   0.00892  -0.0745   0.6452   0.8895
   0.250   0.4578   0.01606   0.00887  -0.0746   0.6425   0.8915
   0.500   0.4853   0.01609   0.00881  -0.0748   0.6402   0.8936
   0.750   0.5124   0.01613   0.00876  -0.0749   0.6381   0.8958
   1.000   0.5282   0.01614   0.00881  -0.0729   0.6347   0.8991
   1.250   0.5456   0.01615   0.00881  -0.0713   0.6314   0.9023
   1.500   0.5702   0.01616   0.00878  -0.0710   0.6286   0.9037
   1.750   0.5974   0.01617   0.00874  -0.0711   0.6260   0.9049
   2.000   0.6243   0.01620   0.00872  -0.0713   0.6236   0.9061
   2.250   0.6415   0.01623   0.00882  -0.0695   0.6197   0.9080
   2.500   0.6626   0.01625   0.00885  -0.0686   0.6161   0.9099
   2.750   0.6867   0.01625   0.00884  -0.0682   0.6131   0.9112
   3.000   0.7136   0.01624   0.00880  -0.0684   0.6106   0.9123
   3.250   0.7305   0.01629   0.00891  -0.0667   0.6066   0.9145
   3.500   0.7503   0.01632   0.00897  -0.0656   0.6024   0.9160
   3.750   0.7745   0.01631   0.00896  -0.0653   0.5990   0.9171
   4.000   0.8018   0.01626   0.00891  -0.0656   0.5963   0.9178
   4.250   0.8177   0.01632   0.00906  -0.0637   0.5913   0.9192
   4.500   0.8382   0.01632   0.00909  -0.0626   0.5870   0.9207
   4.750   0.8632   0.01626   0.00903  -0.0624   0.5834   0.9216
   5.000   0.8850   0.01626   0.00909  -0.0616   0.5793   0.9227
   5.250   0.9029   0.01632   0.00921  -0.0602   0.5739   0.9241
   5.500   0.9265   0.01627   0.00918  -0.0597   0.5695   0.9251
   5.750   0.9504   0.01624   0.00917  -0.0593   0.5651   0.9261
   6.000   0.9661   0.01634   0.00935  -0.0576   0.5588   0.9277
   6.250   0.9886   0.01631   0.00933  -0.0569   0.5538   0.9292
   6.500   1.0085   0.01635   0.00941  -0.0558   0.5485   0.9308
   6.750   1.0233   0.01649   0.00962  -0.0539   0.5417   0.9323
   7.000   1.0473   0.01647   0.00960  -0.0535   0.5361   0.9333
   7.250   1.0589   0.01672   0.00995  -0.0511   0.5285   0.9351
   7.500   1.0787   0.01682   0.01008  -0.0500   0.5216   0.9365
   7.750   1.0927   0.01708   0.01042  -0.0481   0.5134   0.9384
   8.000   1.1116   0.01725   0.01060  -0.0471   0.5054   0.9401
   8.250   1.1246   0.01760   0.01103  -0.0452   0.4962   0.9422
   8.500   1.1424   0.01785   0.01130  -0.0441   0.4873   0.9440
   8.750   1.1550   0.01825   0.01176  -0.0422   0.4771   0.9465
   9.000   1.1678   0.01866   0.01221  -0.0404   0.4669   0.9493
   9.250   1.1821   0.01909   0.01265  -0.0390   0.4563   0.9521
   9.500   1.1934   0.01969   0.01329  -0.0373   0.4444   0.9551
   9.750   1.2045   0.02038   0.01402  -0.0357   0.4322   0.9583
  10.000   1.2160   0.02113   0.01480  -0.0343   0.4194   0.9619
  10.250   1.2271   0.02201   0.01570  -0.0332   0.4056   0.9664
  10.750   1.2484   0.02414   0.01786  -0.0315   0.3766   0.9816
  11.000   1.2540   0.02535   0.01907  -0.0300   0.3624   1.0000
  11.250   1.2593   0.02677   0.02049  -0.0286   0.3474   1.0000
  11.500   1.2641   0.02828   0.02199  -0.0274   0.3325   1.0000
  11.750   1.2684   0.02988   0.02359  -0.0262   0.3177   1.0000
  12.000   1.2716   0.03162   0.02532  -0.0250   0.3025   1.0000
  12.250   1.2745   0.03344   0.02712  -0.0239   0.2876   1.0000
  12.500   1.2770   0.03536   0.02903  -0.0229   0.2728   1.0000
  12.750   1.2797   0.03733   0.03101  -0.0220   0.2586   1.0000
  13.000   1.2822   0.03937   0.03304  -0.0211   0.2449   1.0000
  13.250   1.2843   0.04150   0.03516  -0.0204   0.2314   1.0000
  13.500   1.2859   0.04372   0.03737  -0.0197   0.2182   1.0000
  13.750   1.2871   0.04603   0.03968  -0.0191   0.2050   1.0000
  14.000   1.2874   0.04848   0.04212  -0.0185   0.1920   1.0000
  14.250   1.2879   0.05098   0.04462  -0.0180   0.1788   1.0000
  14.500   1.2887   0.05353   0.04716  -0.0177   0.1658   1.0000
  14.750   1.2892   0.05616   0.04980  -0.0174   0.1535   1.0000
  15.000   1.2895   0.05888   0.05253  -0.0172   0.1420   1.0000
  15.250   1.2892   0.06172   0.05537  -0.0171   0.1311   1.0000
  15.500   1.2881   0.06474   0.05840  -0.0172   0.1209   1.0000
  15.750   1.2879   0.06772   0.06141  -0.0173   0.1108   1.0000
  16.000   1.2889   0.07062   0.06435  -0.0175   0.1019   1.0000
  16.250   1.2880   0.07381   0.06757  -0.0178   0.0940   1.0000
  16.500   1.2865   0.07714   0.07092  -0.0183   0.0860   1.0000
  16.750   1.2865   0.08034   0.07418  -0.0188   0.0786   1.0000
  17.000   1.2844   0.08386   0.07774  -0.0194   0.0723   1.0000
  17.250   1.2830   0.08735   0.08128  -0.0201   0.0658   1.0000
  17.500   1.2812   0.09094   0.08494  -0.0210   0.0600   1.0000
  18.000   1.2760   0.09854   0.09267  -0.0230   0.0498   1.0000
  18.250   1.2725   0.10255   0.09673  -0.0243   0.0454   1.0000
  18.500   1.2696   0.10651   0.10076  -0.0256   0.0415   1.0000
  18.750   1.2660   0.11062   0.10494  -0.0270   0.0380   1.0000
  19.000   1.2625   0.11478   0.10918  -0.0286   0.0348   1.0000
  19.250   1.2590   0.11896   0.11345  -0.0303   0.0320   1.0000
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