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EPPLER 1211 AIRFOIL (e1211-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 1211 AIRFOIL (e1211-il)
Reynolds number: 500,000
Max Cl/Cd: 89.58 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e1211-il-500000-n5.txt
Download as CSV file: xf-e1211-il-500000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.500  -0.6867   0.09021   0.08622  -0.0512   1.0000   0.0231
 -15.250  -0.6969   0.08540   0.08137  -0.0536   1.0000   0.0234
 -15.000  -0.7055   0.08092   0.07685  -0.0558   1.0000   0.0236
 -14.750  -0.7200   0.07573   0.07160  -0.0585   1.0000   0.0239
 -14.500  -0.7374   0.07037   0.06618  -0.0613   1.0000   0.0241
 -14.250  -0.7622   0.06445   0.06019  -0.0644   1.0000   0.0242
 -14.000  -0.7959   0.05771   0.05335  -0.0680   1.0000   0.0241
 -13.750  -0.8471   0.04925   0.04477  -0.0724   1.0000   0.0238
 -13.500  -0.9226   0.03819   0.03349  -0.0780   1.0000   0.0231
 -13.250  -0.9826   0.02832   0.02324  -0.0849   0.9993   0.0227
 -13.000  -0.9569   0.02582   0.02062  -0.0894   0.9939   0.0235
 -12.750  -0.9320   0.02417   0.01888  -0.0917   0.9876   0.0242
 -12.250  -0.8892   0.02163   0.01619  -0.0930   0.9611   0.0261
 -12.000  -0.8584   0.02049   0.01498  -0.0949   0.9410   0.0277
 -11.750  -0.8065   0.01918   0.01359  -0.1009   0.9240   0.0309
 -11.500  -0.7495   0.01793   0.01225  -0.1078   0.8956   0.0363
 -11.250  -0.7175   0.01716   0.01130  -0.1093   0.8525   0.0417
 -11.000  -0.6957   0.01663   0.01062  -0.1086   0.8191   0.0465
 -10.750  -0.6744   0.01615   0.01002  -0.1076   0.7928   0.0513
 -10.500  -0.6524   0.01570   0.00947  -0.1068   0.7704   0.0565
 -10.250  -0.6295   0.01530   0.00897  -0.1060   0.7506   0.0615
 -10.000  -0.6059   0.01491   0.00851  -0.1053   0.7323   0.0669
  -9.750  -0.5817   0.01456   0.00809  -0.1046   0.7157   0.0723
  -9.500  -0.5570   0.01422   0.00768  -0.1040   0.7007   0.0778
  -9.250  -0.5321   0.01393   0.00732  -0.1035   0.6857   0.0830
  -9.000  -0.5062   0.01367   0.00700  -0.1030   0.6717   0.0879
  -8.750  -0.4803   0.01342   0.00669  -0.1025   0.6589   0.0929
  -8.500  -0.4541   0.01320   0.00641  -0.1020   0.6456   0.0975
  -8.250  -0.4274   0.01300   0.00615  -0.1016   0.6337   0.1030
  -7.750  -0.3737   0.01264   0.00569  -0.1008   0.6105   0.1138
  -7.500  -0.3469   0.01249   0.00549  -0.1004   0.5992   0.1191
  -7.250  -0.3192   0.01235   0.00530  -0.1001   0.5888   0.1236
  -7.000  -0.2921   0.01224   0.00514  -0.0997   0.5783   0.1284
  -6.750  -0.2641   0.01213   0.00498  -0.0994   0.5681   0.1327
  -6.250  -0.2086   0.01194   0.00471  -0.0988   0.5492   0.1416
  -6.000  -0.1809   0.01189   0.00457  -0.0985   0.5392   0.1452
  -5.750  -0.1529   0.01179   0.00445  -0.0982   0.5305   0.1490
  -5.500  -0.1249   0.01173   0.00434  -0.0979   0.5215   0.1524
  -5.250  -0.0969   0.01169   0.00423  -0.0976   0.5131   0.1557
  -5.000  -0.0687   0.01162   0.00411  -0.0973   0.5041   0.1586
  -4.750  -0.0410   0.01157   0.00402  -0.0970   0.4959   0.1617
  -4.500  -0.0126   0.01151   0.00393  -0.0968   0.4885   0.1649
  -4.250   0.0155   0.01148   0.00384  -0.0965   0.4802   0.1680
  -4.000   0.0438   0.01147   0.00376  -0.0962   0.4725   0.1704
  -3.750   0.0719   0.01140   0.00367  -0.0960   0.4647   0.1734
  -3.500   0.0998   0.01138   0.00361  -0.0957   0.4575   0.1765
  -3.250   0.1282   0.01135   0.00356  -0.0955   0.4512   0.1794
  -3.000   0.1565   0.01134   0.00350  -0.0952   0.4435   0.1823
  -2.750   0.1844   0.01137   0.00345  -0.0949   0.4362   0.1848
  -2.500   0.2127   0.01131   0.00339  -0.0947   0.4297   0.1876
  -2.250   0.2408   0.01129   0.00336  -0.0945   0.4231   0.1908
  -2.000   0.2686   0.01132   0.00334  -0.0942   0.4168   0.1940
  -1.750   0.2971   0.01131   0.00331  -0.0940   0.4108   0.1970
  -1.500   0.3252   0.01134   0.00329  -0.0937   0.4038   0.1997
  -1.250   0.3529   0.01137   0.00328  -0.0934   0.3976   0.2026
  -1.000   0.3811   0.01135   0.00327  -0.0932   0.3923   0.2061
  -0.750   0.4091   0.01136   0.00327  -0.0929   0.3864   0.2094
  -0.500   0.4367   0.01142   0.00329  -0.0926   0.3803   0.2131
  -0.250   0.4649   0.01145   0.00330  -0.0924   0.3750   0.2164
   0.000   0.4928   0.01149   0.00332  -0.0921   0.3692   0.2196
   0.250   0.5203   0.01153   0.00335  -0.0918   0.3639   0.2237
   0.500   0.5480   0.01158   0.00339  -0.0915   0.3591   0.2282
   0.750   0.5759   0.01162   0.00343  -0.0913   0.3541   0.2327
   1.250   0.6306   0.01176   0.00354  -0.0906   0.3435   0.2418
   1.500   0.6583   0.01181   0.00361  -0.0904   0.3396   0.2476
   1.750   0.6859   0.01187   0.00367  -0.0901   0.3350   0.2536
   2.000   0.7131   0.01195   0.00376  -0.0898   0.3300   0.2606
   2.250   0.7397   0.01205   0.00385  -0.0894   0.3252   0.2685
   2.750   0.7944   0.01218   0.00404  -0.0888   0.3176   0.2866
   3.000   0.8213   0.01227   0.00415  -0.0885   0.3135   0.2981
   3.250   0.8475   0.01238   0.00428  -0.0880   0.3092   0.3135
   3.500   0.8741   0.01247   0.00442  -0.0877   0.3055   0.3304
   3.750   0.9010   0.01253   0.00454  -0.0873   0.3017   0.3496
   4.000   0.9274   0.01262   0.00469  -0.0869   0.2980   0.3725
   4.250   0.9533   0.01271   0.00485  -0.0865   0.2944   0.4010
   4.500   0.9786   0.01282   0.00504  -0.0860   0.2907   0.4378
   4.750   1.0048   0.01286   0.00522  -0.0856   0.2878   0.4815
   5.000   1.0306   0.01290   0.00540  -0.0851   0.2842   0.5313
   5.250   1.0557   0.01296   0.00560  -0.0846   0.2806   0.5893
   5.500   1.0797   0.01300   0.00583  -0.0838   0.2772   0.6623
   5.750   1.1012   0.01299   0.00609  -0.0825   0.2741   0.7633
   6.000   1.1264   0.01278   0.00627  -0.0816   0.2716   1.0000
   6.250   1.1517   0.01297   0.00646  -0.0810   0.2688   1.0000
   6.500   1.1762   0.01319   0.00667  -0.0804   0.2657   1.0000
   6.750   1.2000   0.01344   0.00689  -0.0797   0.2624   1.0000
   7.000   1.2228   0.01372   0.00713  -0.0788   0.2591   1.0000
   7.250   1.2460   0.01397   0.00738  -0.0779   0.2565   1.0000
   7.500   1.2698   0.01419   0.00761  -0.0772   0.2541   1.0000
   7.750   1.2927   0.01443   0.00786  -0.0763   0.2516   1.0000
   8.000   1.3147   0.01470   0.00813  -0.0753   0.2488   1.0000
   8.250   1.3347   0.01498   0.00840  -0.0740   0.2462   1.0000
   8.500   1.3528   0.01531   0.00871  -0.0723   0.2434   1.0000
   8.750   1.3713   0.01563   0.00903  -0.0707   0.2409   1.0000
   9.000   1.3912   0.01590   0.00933  -0.0694   0.2387   1.0000
   9.250   1.4102   0.01621   0.00967  -0.0680   0.2363   1.0000
   9.500   1.4282   0.01656   0.01003  -0.0665   0.2339   1.0000
   9.750   1.4453   0.01695   0.01043  -0.0649   0.2316   1.0000
  10.000   1.4610   0.01740   0.01088  -0.0632   0.2293   1.0000
  10.250   1.4754   0.01791   0.01139  -0.0614   0.2269   1.0000
  10.500   1.4929   0.01832   0.01184  -0.0600   0.2252   1.0000
  10.750   1.5095   0.01877   0.01234  -0.0586   0.2230   1.0000
  11.000   1.5249   0.01929   0.01289  -0.0571   0.2206   1.0000
  11.250   1.5390   0.01989   0.01352  -0.0556   0.2184   1.0000
  11.500   1.5517   0.02057   0.01423  -0.0540   0.2163   1.0000
  11.750   1.5629   0.02137   0.01504  -0.0523   0.2142   1.0000
  12.000   1.5730   0.02228   0.01597  -0.0508   0.2120   1.0000
  12.250   1.5872   0.02301   0.01676  -0.0496   0.2103   1.0000
  12.500   1.6000   0.02386   0.01767  -0.0485   0.2083   1.0000
  12.750   1.6116   0.02482   0.01868  -0.0473   0.2062   1.0000
  13.000   1.6215   0.02592   0.01982  -0.0462   0.2040   1.0000
  13.250   1.6296   0.02720   0.02113  -0.0451   0.2017   1.0000
  13.500   1.6359   0.02866   0.02261  -0.0440   0.1994   1.0000
  13.750   1.6439   0.03007   0.02407  -0.0431   0.1974   1.0000
  14.000   1.6539   0.03136   0.02543  -0.0424   0.1955   1.0000
  14.250   1.6622   0.03284   0.02698  -0.0418   0.1933   1.0000
  14.500   1.6683   0.03452   0.02871  -0.0411   0.1909   1.0000
  14.750   1.6727   0.03640   0.03064  -0.0406   0.1887   1.0000
  15.000   1.6745   0.03856   0.03283  -0.0400   0.1864   1.0000
  15.250   1.6766   0.04075   0.03506  -0.0396   0.1844   1.0000
  15.500   1.6827   0.04263   0.03703  -0.0394   0.1826   1.0000
  15.750   1.6870   0.04472   0.03920  -0.0392   0.1805   1.0000
  16.000   1.6897   0.04703   0.04158  -0.0391   0.1783   1.0000
  16.250   1.6896   0.04968   0.04429  -0.0391   0.1760   1.0000
  16.500   1.6873   0.05263   0.04728  -0.0392   0.1738   1.0000
  16.750   1.6846   0.05569   0.05038  -0.0395   0.1716   1.0000
  17.000   1.6878   0.05818   0.05296  -0.0398   0.1697   1.0000
  17.250   1.6877   0.06110   0.05598  -0.0402   0.1674   1.0000
  17.500   1.6859   0.06427   0.05922  -0.0407   0.1649   1.0000
  17.750   1.6818   0.06777   0.06277  -0.0415   0.1625   1.0000
  18.000   1.6742   0.07178   0.06682  -0.0424   0.1600   1.0000
  18.250   1.6726   0.07511   0.07024  -0.0432   0.1577   1.0000
  18.500   1.6697   0.07867   0.07389  -0.0442   0.1551   1.0000
  18.750   1.6631   0.08278   0.07807  -0.0454   0.1523   1.0000
  19.000   1.6545   0.08720   0.08254  -0.0468   0.1494   1.0000
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