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EPPLER 1211 AIRFOIL (e1211-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 1211 AIRFOIL (e1211-il)
Reynolds number: 500,000
Max Cl/Cd: 88.97 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e1211-il-500000.txt
Download as CSV file: xf-e1211-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 1211 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
  ------ -------- --------- --------- -------- -------- --------
 -16.000  -0.7277   0.08972   0.08575  -0.0531   1.0000   0.0298
 -15.750  -0.7294   0.08626   0.08226  -0.0547   1.0000   0.0302
 -15.500  -0.7316   0.08275   0.07874  -0.0563   1.0000   0.0307
 -15.250  -0.7354   0.07907   0.07503  -0.0580   1.0000   0.0313
 -15.000  -0.7410   0.07520   0.07113  -0.0598   1.0000   0.0316
 -14.750  -0.7480   0.07126   0.06714  -0.0617   1.0000   0.0321
 -14.500  -0.7615   0.06676   0.06261  -0.0639   1.0000   0.0324
 -14.250  -0.7824   0.06158   0.05741  -0.0666   1.0000   0.0328
 -14.000  -0.8090   0.05585   0.05162  -0.0695   1.0000   0.0329
 -13.750  -0.8466   0.04906   0.04472  -0.0729   1.0000   0.0328
 -13.500  -0.8891   0.04192   0.03746  -0.0761   1.0000   0.0324
 -13.250  -0.9720   0.02982   0.02503  -0.0837   1.0000   0.0314
 -13.000  -0.9807   0.02725   0.02233  -0.0828   1.0000   0.0318
 -12.750  -0.9807   0.02551   0.02050  -0.0813   1.0000   0.0324
 -12.500  -0.9785   0.02391   0.01884  -0.0796   1.0000   0.0333
 -12.250  -0.9597   0.02253   0.01740  -0.0801   0.9986   0.0348
 -12.000  -0.9226   0.02107   0.01589  -0.0837   0.9943   0.0373
 -11.750  -0.8865   0.01970   0.01447  -0.0868   0.9897   0.0413
 -11.500  -0.8520   0.01835   0.01312  -0.0895   0.9834   0.0483
 -11.250  -0.8164   0.01715   0.01194  -0.0920   0.9772   0.0585
 -11.000  -0.7839   0.01628   0.01108  -0.0935   0.9666   0.0674
 -10.750  -0.7534   0.01557   0.01038  -0.0942   0.9515   0.0748
 -10.500  -0.7159   0.01495   0.00975  -0.0962   0.9375   0.0820
 -10.250  -0.6667   0.01438   0.00915  -0.1005   0.9241   0.0893
 -10.000  -0.6141   0.01387   0.00858  -0.1053   0.9034   0.0966
  -9.750  -0.5745   0.01358   0.00815  -0.1074   0.8706   0.1027
  -9.250  -0.5204   0.01328   0.00755  -0.1066   0.8126   0.1123
  -9.000  -0.4953   0.01310   0.00729  -0.1059   0.7897   0.1166
  -8.750  -0.4693   0.01301   0.00707  -0.1053   0.7694   0.1211
  -8.500  -0.4437   0.01287   0.00684  -0.1046   0.7507   0.1252
  -8.250  -0.4172   0.01278   0.00668  -0.1041   0.7333   0.1297
  -8.000  -0.3902   0.01271   0.00650  -0.1036   0.7175   0.1341
  -7.750  -0.3638   0.01262   0.00637  -0.1030   0.7025   0.1385
  -7.500  -0.3366   0.01262   0.00625  -0.1026   0.6878   0.1428
  -7.250  -0.3094   0.01250   0.00607  -0.1021   0.6745   0.1468
  -7.000  -0.2823   0.01246   0.00598  -0.1017   0.6614   0.1507
  -6.750  -0.2546   0.01246   0.00589  -0.1013   0.6485   0.1546
  -6.500  -0.2270   0.01241   0.00574  -0.1009   0.6369   0.1583
  -6.250  -0.1998   0.01232   0.00564  -0.1005   0.6249   0.1622
  -6.000  -0.1719   0.01232   0.00558  -0.1002   0.6138   0.1659
  -5.750  -0.1441   0.01235   0.00549  -0.0998   0.6025   0.1693
  -5.500  -0.1164   0.01219   0.00528  -0.0995   0.5924   0.1726
  -5.250  -0.0890   0.01211   0.00517  -0.0991   0.5817   0.1759
  -5.000  -0.0609   0.01208   0.00511  -0.0988   0.5719   0.1792
  -4.750  -0.0330   0.01208   0.00502  -0.0984   0.5620   0.1824
  -4.500  -0.0047   0.01210   0.00494  -0.0982   0.5530   0.1849
  -4.250   0.0226   0.01187   0.00470  -0.0978   0.5434   0.1887
  -4.000   0.0504   0.01183   0.00463  -0.0975   0.5345   0.1919
  -3.750   0.0787   0.01180   0.00457  -0.0972   0.5256   0.1951
  -3.500   0.1064   0.01182   0.00449  -0.0969   0.5171   0.1982
  -3.250   0.1351   0.01182   0.00444  -0.0966   0.5091   0.2006
  -3.000   0.1624   0.01164   0.00423  -0.0963   0.5005   0.2044
  -2.750   0.1902   0.01159   0.00417  -0.0960   0.4927   0.2078
  -2.500   0.2184   0.01157   0.00413  -0.0957   0.4846   0.2112
  -2.250   0.2461   0.01160   0.00408  -0.0954   0.4770   0.2144
  -2.000   0.2747   0.01160   0.00405  -0.0952   0.4699   0.2172
  -1.750   0.3023   0.01150   0.00392  -0.0949   0.4622   0.2210
  -1.500   0.3297   0.01147   0.00387  -0.0945   0.4549   0.2248
  -1.250   0.3580   0.01145   0.00385  -0.0943   0.4479   0.2286
  -1.000   0.3858   0.01149   0.00384  -0.0940   0.4410   0.2324
  -0.750   0.4137   0.01155   0.00384  -0.0937   0.4344   0.2355
  -0.500   0.4416   0.01146   0.00377  -0.0935   0.4278   0.2400
  -0.250   0.4689   0.01147   0.00376  -0.0931   0.4209   0.2449
   0.000   0.4966   0.01151   0.00379  -0.0928   0.4148   0.2495
   0.250   0.5248   0.01154   0.00380  -0.0926   0.4088   0.2538
   0.500   0.5521   0.01155   0.00379  -0.0923   0.4026   0.2590
   0.750   0.5792   0.01160   0.00384  -0.0919   0.3966   0.2654
   1.000   0.6073   0.01161   0.00387  -0.0917   0.3910   0.2717
   1.250   0.6347   0.01167   0.00390  -0.0914   0.3852   0.2781
   1.500   0.6612   0.01176   0.00398  -0.0909   0.3794   0.2866
   1.750   0.6893   0.01178   0.00404  -0.0907   0.3748   0.2954
   2.000   0.7166   0.01179   0.00410  -0.0904   0.3693   0.3078
   2.250   0.7433   0.01188   0.00418  -0.0900   0.3639   0.3214
   2.500   0.7700   0.01196   0.00430  -0.0897   0.3591   0.3389
   2.750   0.7975   0.01195   0.00440  -0.0894   0.3548   0.3631
   3.000   0.8243   0.01197   0.00452  -0.0891   0.3500   0.3961
   3.250   0.8502   0.01203   0.00466  -0.0887   0.3451   0.4397
   3.500   0.8764   0.01206   0.00484  -0.0883   0.3407   0.4949
   3.750   0.9029   0.01199   0.00500  -0.0879   0.3366   0.5642
   4.000   0.9281   0.01193   0.00518  -0.0873   0.3325   0.6492
   4.250   0.9506   0.01185   0.00539  -0.0860   0.3284   0.7587
   4.500   0.9767   0.01169   0.00559  -0.0851   0.3240   1.0000
   4.750   1.0036   0.01182   0.00573  -0.0848   0.3206   1.0000
   5.000   1.0299   0.01198   0.00587  -0.0844   0.3166   1.0000
   5.250   1.0553   0.01219   0.00603  -0.0839   0.3127   1.0000
   5.500   1.0798   0.01249   0.00625  -0.0832   0.3086   1.0000
   5.750   1.1053   0.01271   0.00646  -0.0827   0.3054   1.0000
   6.000   1.1311   0.01288   0.00664  -0.0822   0.3022   1.0000
   6.250   1.1562   0.01308   0.00683  -0.0816   0.2987   1.0000
   6.500   1.1804   0.01333   0.00703  -0.0809   0.2952   1.0000
   6.750   1.2034   0.01367   0.00731  -0.0801   0.2912   1.0000
   7.000   1.2277   0.01391   0.00756  -0.0794   0.2883   1.0000
   7.250   1.2521   0.01411   0.00778  -0.0788   0.2855   1.0000
   7.500   1.2758   0.01434   0.00802  -0.0780   0.2824   1.0000
   7.750   1.2985   0.01461   0.00827  -0.0771   0.2794   1.0000
   8.000   1.3199   0.01495   0.00857  -0.0760   0.2762   1.0000
   8.250   1.3412   0.01534   0.00894  -0.0750   0.2729   1.0000
   8.500   1.3632   0.01556   0.00920  -0.0740   0.2705   1.0000
   8.750   1.3834   0.01580   0.00947  -0.0726   0.2676   1.0000
   9.000   1.4026   0.01608   0.00977  -0.0712   0.2649   1.0000
   9.250   1.4204   0.01643   0.01010  -0.0695   0.2623   1.0000
   9.500   1.4373   0.01687   0.01051  -0.0678   0.2594   1.0000
   9.750   1.4551   0.01732   0.01096  -0.0664   0.2568   1.0000
  10.000   1.4733   0.01764   0.01134  -0.0649   0.2547   1.0000
  10.250   1.4909   0.01798   0.01173  -0.0634   0.2523   1.0000
  10.500   1.5078   0.01838   0.01215  -0.0619   0.2498   1.0000
  10.750   1.5234   0.01883   0.01262  -0.0602   0.2472   1.0000
  11.000   1.5380   0.01939   0.01316  -0.0586   0.2448   1.0000
  11.250   1.5530   0.02009   0.01382  -0.0570   0.2418   1.0000
  11.500   1.5679   0.02057   0.01440  -0.0555   0.2402   1.0000
  11.750   1.5823   0.02113   0.01502  -0.0540   0.2381   1.0000
  12.000   1.5960   0.02174   0.01569  -0.0526   0.2358   1.0000
  12.250   1.6091   0.02243   0.01641  -0.0512   0.2336   1.0000
  12.500   1.6212   0.02321   0.01721  -0.0497   0.2314   1.0000
  12.750   1.6323   0.02411   0.01810  -0.0483   0.2290   1.0000
  13.000   1.6446   0.02504   0.01903  -0.0471   0.2263   1.0000
  13.250   1.6554   0.02596   0.02005  -0.0459   0.2246   1.0000
  13.500   1.6658   0.02697   0.02113  -0.0447   0.2225   1.0000
  13.750   1.6758   0.02805   0.02228  -0.0437   0.2202   1.0000
  14.000   1.6850   0.02922   0.02350  -0.0427   0.2180   1.0000
  14.250   1.6933   0.03051   0.02480  -0.0418   0.2157   1.0000
  14.500   1.7021   0.03182   0.02609  -0.0408   0.2130   1.0000
  14.750   1.7105   0.03321   0.02754  -0.0400   0.2112   1.0000
  15.000   1.7167   0.03478   0.02923  -0.0394   0.2092   1.0000
  15.250   1.7233   0.03638   0.03091  -0.0388   0.2072   1.0000
  15.500   1.7290   0.03810   0.03269  -0.0383   0.2050   1.0000
  15.750   1.7340   0.03991   0.03455  -0.0379   0.2029   1.0000
  16.000   1.7390   0.04174   0.03638  -0.0374   0.2006   1.0000
  16.250   1.7467   0.04334   0.03797  -0.0369   0.1980   1.0000
  16.500   1.7479   0.04570   0.04046  -0.0368   0.1963   1.0000
  16.750   1.7492   0.04811   0.04298  -0.0368   0.1942   1.0000
  17.000   1.7508   0.05055   0.04551  -0.0369   0.1919   1.0000
  17.250   1.7517   0.05311   0.04813  -0.0371   0.1897   1.0000
  17.500   1.7538   0.05555   0.05057  -0.0372   0.1872   1.0000
  17.750   1.7594   0.05753   0.05253  -0.0372   0.1845   1.0000
  18.000   1.7541   0.06107   0.05623  -0.0379   0.1826   1.0000
  18.250   1.7507   0.06443   0.05971  -0.0386   0.1802   1.0000
  18.500   1.7474   0.06783   0.06319  -0.0395   0.1776   1.0000
  18.750   1.7448   0.07114   0.06652  -0.0403   0.1750   1.0000
  19.000   1.7495   0.07338   0.06872  -0.0406   0.1720   1.0000
  19.250   1.7377   0.07816   0.07367  -0.0422   0.1696   1.0000
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