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EPPLER 1211 AIRFOIL (e1211-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 1211 AIRFOIL (e1211-il)
Reynolds number: 100,000
Max Cl/Cd: 44.03 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e1211-il-100000-n5.txt
Download as CSV file: xf-e1211-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.4209   0.08587   0.08029  -0.0512   1.0000   0.0872
 -11.250  -0.6801   0.04571   0.03994  -0.0741   1.0000   0.0949
 -11.000  -0.7329   0.03981   0.03393  -0.0755   1.0000   0.0947
 -10.750  -0.7389   0.03833   0.03250  -0.0738   1.0000   0.0968
 -10.500  -0.7210   0.03584   0.02982  -0.0776   0.9905   0.1021
 -10.250  -0.6861   0.03489   0.02884  -0.0810   0.9758   0.1078
 -10.000  -0.6586   0.03334   0.02711  -0.0839   0.9554   0.1143
  -9.750  -0.6262   0.03244   0.02605  -0.0865   0.9375   0.1213
  -9.500  -0.5853   0.03272   0.02640  -0.0886   0.9226   0.1269
  -9.250  -0.5518   0.03104   0.02437  -0.0920   0.9056   0.1339
  -9.000  -0.5090   0.03123   0.02462  -0.0941   0.8895   0.1378
  -8.750  -0.4773   0.02947   0.02241  -0.0969   0.8705   0.1441
  -8.500  -0.4392   0.02936   0.02229  -0.0985   0.8515   0.1476
  -8.250  -0.4064   0.02894   0.02173  -0.0995   0.8319   0.1518
  -8.000  -0.3820   0.02756   0.01989  -0.1003   0.8124   0.1575
  -7.750  -0.3512   0.02758   0.01990  -0.1003   0.7941   0.1604
  -7.500  -0.3244   0.02729   0.01948  -0.1001   0.7762   0.1642
  -7.250  -0.3012   0.02634   0.01815  -0.1000   0.7595   0.1696
  -7.000  -0.2745   0.02603   0.01775  -0.0997   0.7440   0.1729
  -6.750  -0.2471   0.02586   0.01749  -0.0994   0.7297   0.1763
  -6.500  -0.2222   0.02540   0.01686  -0.0990   0.7148   0.1807
  -6.250  -0.1977   0.02467   0.01576  -0.0987   0.7016   0.1856
  -6.000  -0.1710   0.02450   0.01559  -0.0982   0.6887   0.1885
  -5.750  -0.1450   0.02427   0.01529  -0.0977   0.6758   0.1921
  -5.500  -0.1189   0.02389   0.01467  -0.0973   0.6645   0.1965
  -5.250  -0.0937   0.02337   0.01388  -0.0970   0.6521   0.2012
  -5.000  -0.0670   0.02314   0.01362  -0.0965   0.6416   0.2042
  -4.750  -0.0410   0.02292   0.01337  -0.0960   0.6296   0.2078
  -4.500  -0.0144   0.02266   0.01292  -0.0956   0.6199   0.2121
  -4.250   0.0117   0.02232   0.01238  -0.0952   0.6087   0.2167
  -4.000   0.0384   0.02204   0.01197  -0.0948   0.5997   0.2202
  -3.750   0.0646   0.02185   0.01180  -0.0943   0.5887   0.2238
  -3.500   0.0914   0.02167   0.01149  -0.0939   0.5800   0.2280
  -3.250   0.1180   0.02145   0.01116  -0.0935   0.5700   0.2326
  -3.000   0.1448   0.02124   0.01076  -0.0931   0.5611   0.2369
  -2.750   0.1713   0.02106   0.01060  -0.0927   0.5522   0.2406
  -2.500   0.1979   0.02092   0.01043  -0.0922   0.5432   0.2448
  -2.250   0.2249   0.02081   0.01018  -0.0918   0.5355   0.2496
  -2.000   0.2517   0.02069   0.00996  -0.0914   0.5263   0.2546
  -1.750   0.2783   0.02055   0.00977  -0.0910   0.5188   0.2587
  -1.500   0.3048   0.02047   0.00970  -0.0905   0.5107   0.2633
  -1.250   0.3314   0.02040   0.00959  -0.0901   0.5025   0.2687
  -1.000   0.3587   0.02037   0.00938  -0.0897   0.4959   0.2744
  -0.750   0.3847   0.02029   0.00938  -0.0892   0.4877   0.2793
  -0.500   0.4112   0.02025   0.00933  -0.0887   0.4806   0.2848
  -0.250   0.4380   0.02026   0.00925  -0.0883   0.4742   0.2916
   0.000   0.4641   0.02025   0.00928  -0.0879   0.4664   0.2982
   0.250   0.4903   0.02024   0.00927  -0.0874   0.4599   0.3050
   0.500   0.5169   0.02029   0.00926  -0.0869   0.4539   0.3131
   0.750   0.5427   0.02032   0.00936  -0.0864   0.4469   0.3213
   1.000   0.5687   0.02036   0.00940  -0.0859   0.4407   0.3312
   1.250   0.5951   0.02043   0.00943  -0.0854   0.4351   0.3422
   1.500   0.6205   0.02051   0.00961  -0.0849   0.4284   0.3545
   1.750   0.6462   0.02058   0.00972  -0.0843   0.4225   0.3688
   2.000   0.6724   0.02067   0.00978  -0.0839   0.4177   0.3870
   2.250   0.6971   0.02078   0.01003  -0.0832   0.4115   0.4088
   2.500   0.7223   0.02087   0.01024  -0.0827   0.4056   0.4364
   2.750   0.7480   0.02095   0.01038  -0.0821   0.4006   0.4730
   3.000   0.7730   0.02104   0.01062  -0.0815   0.3959   0.5216
   3.250   0.7960   0.02111   0.01097  -0.0805   0.3903   0.5862
   3.500   0.8175   0.02109   0.01123  -0.0790   0.3853   0.6731
   3.750   0.8364   0.02094   0.01138  -0.0766   0.3811   0.8027
   4.000   0.8699   0.02106   0.01160  -0.0774   0.3760   1.0000
   4.250   0.8940   0.02145   0.01195  -0.0769   0.3708   1.0000
   4.500   0.9187   0.02179   0.01221  -0.0763   0.3662   1.0000
   4.750   0.9442   0.02213   0.01241  -0.0759   0.3622   1.0000
   5.000   0.9680   0.02255   0.01280  -0.0753   0.3578   1.0000
   5.250   0.9907   0.02300   0.01325  -0.0745   0.3530   1.0000
   5.500   1.0143   0.02341   0.01362  -0.0739   0.3487   1.0000
   5.750   1.0387   0.02379   0.01392  -0.0734   0.3451   1.0000
   6.000   1.0633   0.02422   0.01425  -0.0729   0.3416   1.0000
   6.250   1.0833   0.02478   0.01489  -0.0718   0.3370   1.0000
   6.500   1.1047   0.02527   0.01540  -0.0709   0.3327   1.0000
   6.750   1.1273   0.02572   0.01580  -0.0702   0.3290   1.0000
   7.000   1.1514   0.02615   0.01615  -0.0696   0.3260   1.0000
   7.250   1.1724   0.02674   0.01675  -0.0688   0.3226   1.0000
   7.500   1.1897   0.02741   0.01751  -0.0674   0.3186   1.0000
   7.750   1.2085   0.02800   0.01813  -0.0663   0.3149   1.0000
   8.000   1.2291   0.02851   0.01861  -0.0654   0.3114   1.0000
   8.250   1.2520   0.02898   0.01902  -0.0647   0.3086   1.0000
   8.500   1.2704   0.02966   0.01973  -0.0636   0.3056   1.0000
   8.750   1.2821   0.03054   0.02074  -0.0617   0.3022   1.0000
   9.000   1.2951   0.03133   0.02161  -0.0600   0.2988   1.0000
   9.250   1.3097   0.03201   0.02231  -0.0584   0.2958   1.0000
   9.500   1.3278   0.03258   0.02285  -0.0572   0.2930   1.0000
   9.750   1.3509   0.03308   0.02327  -0.0567   0.2905   1.0000
  10.000   1.3521   0.03429   0.02465  -0.0538   0.2875   1.0000
  10.250   1.3529   0.03562   0.02613  -0.0511   0.2845   1.0000
  10.500   1.3576   0.03689   0.02749  -0.0491   0.2816   1.0000
  10.750   1.3669   0.03797   0.02862  -0.0476   0.2789   1.0000
  11.000   1.3822   0.03879   0.02944  -0.0466   0.2765   1.0000
  11.250   1.4049   0.03930   0.02989  -0.0462   0.2742   1.0000
  11.500   1.3954   0.04152   0.03229  -0.0439   0.2715   1.0000
  11.750   1.3714   0.04495   0.03597  -0.0417   0.2681   1.0000
  12.000   1.3542   0.04839   0.03958  -0.0405   0.2650   1.0000
  12.250   1.3507   0.05100   0.04227  -0.0399   0.2623   1.0000
  12.500   1.3647   0.05215   0.04343  -0.0394   0.2601   1.0000
  12.750   1.3930   0.05209   0.04331  -0.0390   0.2583   1.0000
  13.250   1.1604   0.08590   0.07790  -0.0475   0.2413   1.0000
  13.500   1.2078   0.08228   0.07423  -0.0454   0.2419   1.0000
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