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EPPLER 1210 AIRFOIL (e1210-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 1210 AIRFOIL (e1210-il)
Reynolds number: 500,000
Max Cl/Cd: 93.21 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e1210-il-500000-n5.txt
Download as CSV file: xf-e1210-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 1210 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.250  -0.5862   0.08952   0.08633  -0.0484   1.0000   0.0199
 -14.000  -0.6071   0.08275   0.07950  -0.0523   1.0000   0.0201
 -13.750  -0.6378   0.07497   0.07165  -0.0571   1.0000   0.0203
 -13.500  -0.6917   0.06454   0.06112  -0.0641   1.0000   0.0200
 -13.250  -0.9143   0.03135   0.02715  -0.0889   1.0000   0.0184
 -13.000  -0.9071   0.02865   0.02429  -0.0901   0.9983   0.0187
 -12.750  -0.8807   0.02635   0.02186  -0.0935   0.9918   0.0192
 -12.250  -0.8341   0.02345   0.01875  -0.0954   0.9644   0.0203
 -12.000  -0.7947   0.02215   0.01730  -0.0990   0.9411   0.0211
 -11.750  -0.7381   0.02066   0.01567  -0.1059   0.9135   0.0222
 -11.500  -0.6994   0.01971   0.01448  -0.1088   0.8674   0.0233
 -11.250  -0.6770   0.01914   0.01368  -0.1081   0.8301   0.0243
 -11.000  -0.6559   0.01858   0.01294  -0.1071   0.8013   0.0252
 -10.750  -0.6341   0.01803   0.01225  -0.1062   0.7778   0.0263
 -10.500  -0.6112   0.01756   0.01163  -0.1054   0.7575   0.0276
 -10.250  -0.5880   0.01708   0.01102  -0.1047   0.7387   0.0290
 -10.000  -0.5641   0.01665   0.01047  -0.1040   0.7216   0.0305
  -9.750  -0.5394   0.01625   0.00996  -0.1033   0.7059   0.0321
  -9.500  -0.5147   0.01585   0.00947  -0.1027   0.6913   0.0339
  -9.250  -0.4894   0.01553   0.00902  -0.1021   0.6769   0.0357
  -9.000  -0.4638   0.01516   0.00859  -0.1016   0.6634   0.0375
  -8.750  -0.4379   0.01487   0.00819  -0.1011   0.6507   0.0394
  -8.500  -0.4120   0.01457   0.00781  -0.1006   0.6380   0.0412
  -8.250  -0.3854   0.01429   0.00746  -0.1001   0.6264   0.0432
  -8.000  -0.3591   0.01405   0.00713  -0.0996   0.6150   0.0452
  -7.750  -0.3322   0.01380   0.00682  -0.0992   0.6035   0.0475
  -7.500  -0.3054   0.01360   0.00653  -0.0988   0.5928   0.0497
  -7.250  -0.2783   0.01338   0.00626  -0.0984   0.5820   0.0521
  -7.000  -0.2511   0.01321   0.00600  -0.0979   0.5721   0.0545
  -6.750  -0.2238   0.01301   0.00577  -0.0976   0.5620   0.0571
  -6.500  -0.1964   0.01287   0.00554  -0.0972   0.5525   0.0600
  -6.250  -0.1689   0.01270   0.00536  -0.0968   0.5428   0.0629
  -6.000  -0.1414   0.01259   0.00516  -0.0965   0.5341   0.0658
  -5.750  -0.1136   0.01243   0.00497  -0.0961   0.5251   0.0682
  -5.500  -0.0861   0.01232   0.00479  -0.0958   0.5160   0.0709
  -5.250  -0.0581   0.01220   0.00461  -0.0954   0.5081   0.0735
  -5.000  -0.0304   0.01208   0.00447  -0.0951   0.4996   0.0761
  -4.750  -0.0025   0.01200   0.00432  -0.0948   0.4919   0.0789
  -4.500   0.0254   0.01189   0.00417  -0.0945   0.4833   0.0816
  -4.250   0.0531   0.01182   0.00406  -0.0941   0.4757   0.0845
  -4.000   0.0813   0.01174   0.00393  -0.0938   0.4689   0.0874
  -3.750   0.1092   0.01166   0.00382  -0.0935   0.4612   0.0902
  -3.500   0.1371   0.01160   0.00373  -0.0932   0.4541   0.0933
  -3.250   0.1652   0.01156   0.00363  -0.0929   0.4466   0.0964
  -3.000   0.1930   0.01150   0.00354  -0.0926   0.4396   0.0994
  -2.750   0.2211   0.01145   0.00347  -0.0923   0.4338   0.1027
  -2.500   0.2493   0.01142   0.00340  -0.0921   0.4271   0.1061
  -2.250   0.2769   0.01140   0.00334  -0.0917   0.4202   0.1094
  -2.000   0.3051   0.01136   0.00329  -0.0915   0.4141   0.1133
  -1.750   0.3331   0.01135   0.00324  -0.0912   0.4076   0.1169
  -1.500   0.3608   0.01134   0.00320  -0.0909   0.4017   0.1209
  -1.250   0.3889   0.01131   0.00318  -0.0906   0.3963   0.1252
  -1.000   0.4169   0.01132   0.00315  -0.0904   0.3901   0.1293
  -0.750   0.4444   0.01133   0.00314  -0.0901   0.3838   0.1343
  -0.500   0.4724   0.01133   0.00314  -0.0898   0.3787   0.1395
  -0.250   0.5004   0.01134   0.00313  -0.0895   0.3733   0.1447
   0.000   0.5279   0.01136   0.00315  -0.0892   0.3676   0.1517
   0.250   0.5556   0.01140   0.00317  -0.0890   0.3624   0.1584
   0.500   0.5834   0.01140   0.00319  -0.0887   0.3571   0.1677
   0.750   0.6109   0.01144   0.00323  -0.0884   0.3520   0.1775
   1.000   0.6381   0.01150   0.00328  -0.0881   0.3470   0.1904
   1.250   0.6658   0.01150   0.00334  -0.0879   0.3426   0.2073
   1.500   0.6933   0.01152   0.00340  -0.0876   0.3375   0.2277
   1.750   0.7202   0.01156   0.00348  -0.0873   0.3327   0.2545
   2.000   0.7472   0.01157   0.00358  -0.0870   0.3288   0.2911
   2.250   0.7745   0.01155   0.00367  -0.0867   0.3248   0.3360
   2.500   0.8013   0.01151   0.00378  -0.0864   0.3203   0.3948
   2.750   0.8275   0.01148   0.00392  -0.0861   0.3158   0.4688
   3.000   0.8532   0.01142   0.00408  -0.0856   0.3119   0.5579
   3.250   0.8785   0.01126   0.00423  -0.0850   0.3087   0.6720
   3.500   0.9001   0.01103   0.00440  -0.0834   0.3052   0.8098
   3.750   0.9356   0.01095   0.00453  -0.0846   0.3010   1.0000
   4.000   0.9614   0.01116   0.00467  -0.0841   0.2970   1.0000
   4.250   0.9879   0.01131   0.00480  -0.0837   0.2938   1.0000
   4.500   1.0143   0.01148   0.00494  -0.0833   0.2903   1.0000
   4.750   1.0403   0.01166   0.00510  -0.0829   0.2868   1.0000
   5.000   1.0659   0.01187   0.00526  -0.0824   0.2835   1.0000
   5.250   1.0909   0.01211   0.00546  -0.0818   0.2803   1.0000
   5.500   1.1170   0.01228   0.00562  -0.0814   0.2776   1.0000
   5.750   1.1427   0.01247   0.00580  -0.0809   0.2744   1.0000
   6.000   1.1678   0.01268   0.00600  -0.0804   0.2710   1.0000
   6.250   1.1924   0.01292   0.00620  -0.0798   0.2677   1.0000
   6.500   1.2163   0.01319   0.00644  -0.0791   0.2647   1.0000
   6.750   1.2412   0.01339   0.00666  -0.0785   0.2624   1.0000
   7.000   1.2659   0.01361   0.00687  -0.0779   0.2598   1.0000
   7.250   1.2900   0.01384   0.00711  -0.0773   0.2569   1.0000
   7.500   1.3133   0.01410   0.00737  -0.0765   0.2539   1.0000
   7.750   1.3357   0.01440   0.00764  -0.0756   0.2509   1.0000
   8.000   1.3578   0.01470   0.00793  -0.0747   0.2482   1.0000
   8.250   1.3810   0.01494   0.00820  -0.0740   0.2459   1.0000
   8.500   1.4034   0.01520   0.00848  -0.0731   0.2435   1.0000
   8.750   1.4248   0.01549   0.00878  -0.0721   0.2409   1.0000
   9.000   1.4445   0.01581   0.00911  -0.0708   0.2384   1.0000
   9.250   1.4618   0.01616   0.00945  -0.0691   0.2359   1.0000
   9.500   1.4784   0.01654   0.00983  -0.0674   0.2335   1.0000
   9.750   1.4974   0.01684   0.01018  -0.0660   0.2313   1.0000
  10.000   1.5152   0.01719   0.01056  -0.0645   0.2291   1.0000
  10.250   1.5322   0.01758   0.01098  -0.0630   0.2269   1.0000
  10.500   1.5479   0.01803   0.01145  -0.0614   0.2246   1.0000
  10.750   1.5623   0.01854   0.01197  -0.0596   0.2224   1.0000
  11.000   1.5750   0.01915   0.01258  -0.0578   0.2201   1.0000
  11.250   1.5902   0.01967   0.01316  -0.0563   0.2183   1.0000
  11.500   1.6054   0.02022   0.01377  -0.0549   0.2163   1.0000
  11.750   1.6193   0.02086   0.01445  -0.0535   0.2142   1.0000
  12.000   1.6319   0.02159   0.01523  -0.0521   0.2120   1.0000
  12.250   1.6430   0.02244   0.01611  -0.0507   0.2098   1.0000
  12.500   1.6524   0.02345   0.01714  -0.0492   0.2077   1.0000
  12.750   1.6606   0.02460   0.01832  -0.0478   0.2055   1.0000
  13.000   1.6733   0.02552   0.01931  -0.0469   0.2038   1.0000
  13.250   1.6844   0.02658   0.02044  -0.0460   0.2015   1.0000
  13.500   1.6939   0.02780   0.02172  -0.0450   0.1994   1.0000
  13.750   1.7016   0.02921   0.02317  -0.0441   0.1970   1.0000
  14.000   1.7068   0.03086   0.02486  -0.0433   0.1946   1.0000
  14.250   1.7104   0.03271   0.02674  -0.0425   0.1924   1.0000
  14.500   1.7190   0.03420   0.02831  -0.0420   0.1905   1.0000
  14.750   1.7260   0.03586   0.03005  -0.0415   0.1884   1.0000
  15.000   1.7308   0.03776   0.03202  -0.0411   0.1860   1.0000
  15.250   1.7333   0.03992   0.03424  -0.0407   0.1837   1.0000
  15.500   1.7339   0.04230   0.03666  -0.0404   0.1816   1.0000
  15.750   1.7324   0.04494   0.03935  -0.0402   0.1795   1.0000
  16.000   1.7366   0.04710   0.04160  -0.0401   0.1777   1.0000
  16.250   1.7391   0.04949   0.04408  -0.0401   0.1756   1.0000
  16.500   1.7400   0.05210   0.04677  -0.0403   0.1735   1.0000
  16.750   1.7382   0.05509   0.04982  -0.0405   0.1710   1.0000
  17.000   1.7335   0.05845   0.05324  -0.0410   0.1685   1.0000
  17.250   1.7291   0.06187   0.05671  -0.0415   0.1662   1.0000
  17.500   1.7292   0.06484   0.05978  -0.0420   0.1641   1.0000
  17.750   1.7275   0.06806   0.06309  -0.0427   0.1617   1.0000
  18.000   1.7217   0.07187   0.06697  -0.0436   0.1590   1.0000
  18.250   1.7133   0.07608   0.07123  -0.0447   0.1564   1.0000
  18.500   1.7073   0.08004   0.07527  -0.0458   0.1539   1.0000
  18.750   1.7029   0.08389   0.07921  -0.0469   0.1510   1.0000
  19.000   1.6950   0.08824   0.08365  -0.0483   0.1481   1.0000
  19.250   1.6842   0.09308   0.08853  -0.0500   0.1451   1.0000
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