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E211 (10.96%) (e211-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: E211 (10.96%) (e211-il)
Reynolds number: 200,000
Max Cl/Cd: 78.87 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e211-il-200000.txt
Download as CSV file: xf-e211-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E211  (10.96%)                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3511   0.09796   0.09463  -0.0373   1.0000   0.0602
  -9.750  -0.3695   0.09322   0.08994  -0.0407   1.0000   0.0610
  -9.500  -0.3822   0.08856   0.08534  -0.0429   1.0000   0.0612
  -9.250  -0.3742   0.08407   0.08087  -0.0397   1.0000   0.0628
  -9.000  -0.3674   0.08170   0.07851  -0.0378   1.0000   0.0640
  -8.750  -0.3676   0.07870   0.07554  -0.0369   1.0000   0.0653
  -8.500  -0.3725   0.07525   0.07213  -0.0366   1.0000   0.0668
  -8.250  -0.3816   0.07147   0.06840  -0.0366   1.0000   0.0681
  -8.000  -0.3958   0.06742   0.06440  -0.0369   1.0000   0.0695
  -7.750  -0.5616   0.06599   0.06252  -0.0500   1.0000   0.0621
  -7.500  -0.5384   0.06512   0.06192  -0.0458   1.0000   0.0642
  -7.250  -0.5363   0.06301   0.05982  -0.0444   1.0000   0.0660
  -7.000  -0.5394   0.05949   0.05623  -0.0446   1.0000   0.0679
  -6.750  -0.5502   0.05686   0.05275  -0.0477   1.0000   0.0743
  -6.500  -0.5454   0.04968   0.04578  -0.0478   1.0000   0.0763
  -6.250  -0.5341   0.04710   0.04321  -0.0470   1.0000   0.0779
  -6.000  -0.5113   0.03198   0.02626  -0.0493   1.0000   0.0374
  -5.750  -0.4895   0.02792   0.02179  -0.0498   1.0000   0.0356
  -5.500  -0.4657   0.02516   0.01859  -0.0497   1.0000   0.0344
  -5.250  -0.4289   0.02282   0.01583  -0.0517   0.9973   0.0339
  -5.000  -0.3901   0.02119   0.01392  -0.0539   0.9943   0.0344
  -4.750  -0.3523   0.02018   0.01274  -0.0560   0.9897   0.0366
  -4.500  -0.3124   0.01939   0.01178  -0.0585   0.9858   0.0382
  -4.250  -0.2764   0.01778   0.01018  -0.0605   0.9818   0.0407
  -4.000  -0.2386   0.01697   0.00937  -0.0628   0.9765   0.0455
  -3.750  -0.1967   0.01613   0.00850  -0.0659   0.9729   0.0572
  -3.500  -0.1613   0.01464   0.00766  -0.0683   0.9672   0.1770
  -3.250  -0.1224   0.01376   0.00736  -0.0714   0.9622   0.3152
  -3.000  -0.0845   0.01309   0.00744  -0.0739   0.9579   0.5073
  -2.500  -0.0109   0.01293   0.00741  -0.0770   0.9449   0.6224
  -2.250   0.0224   0.01283   0.00727  -0.0778   0.9364   0.6512
  -2.000   0.0609   0.01270   0.00714  -0.0795   0.9311   0.6762
  -1.750   0.0944   0.01253   0.00695  -0.0803   0.9228   0.6958
  -1.500   0.1359   0.01229   0.00670  -0.0826   0.9192   0.7141
  -1.250   0.1663   0.01209   0.00650  -0.0827   0.9094   0.7297
  -1.000   0.2078   0.01177   0.00618  -0.0850   0.9058   0.7453
  -0.750   0.2395   0.01154   0.00594  -0.0854   0.8963   0.7593
  -0.500   0.2823   0.01122   0.00563  -0.0879   0.8919   0.7734
  -0.250   0.3153   0.01099   0.00541  -0.0886   0.8814   0.7866
   0.000   0.3533   0.01074   0.00516  -0.0902   0.8727   0.7998
   0.250   0.3917   0.01050   0.00491  -0.0920   0.8631   0.8121
   0.500   0.4247   0.01033   0.00475  -0.0926   0.8499   0.8237
   0.750   0.4573   0.01020   0.00461  -0.0933   0.8359   0.8354
   1.000   0.4883   0.01012   0.00451  -0.0936   0.8212   0.8476
   1.250   0.5175   0.01008   0.00444  -0.0936   0.8060   0.8605
   1.500   0.5447   0.01006   0.00441  -0.0931   0.7906   0.8745
   1.750   0.5699   0.01006   0.00438  -0.0922   0.7753   0.8900
   2.000   0.5936   0.01005   0.00437  -0.0910   0.7601   0.9084
   2.250   0.6187   0.01005   0.00436  -0.0901   0.7448   0.9312
   2.500   0.6514   0.01005   0.00436  -0.0909   0.7284   0.9588
   2.750   0.6937   0.01010   0.00439  -0.0941   0.7105   1.0000
   3.000   0.7220   0.01027   0.00450  -0.0946   0.6939   1.0000
   3.250   0.7501   0.01045   0.00462  -0.0949   0.6774   1.0000
   3.500   0.7774   0.01064   0.00475  -0.0949   0.6607   1.0000
   3.750   0.8040   0.01084   0.00489  -0.0947   0.6437   1.0000
   4.000   0.8302   0.01105   0.00505  -0.0944   0.6268   1.0000
   4.250   0.8553   0.01124   0.00524  -0.0938   0.6090   1.0000
   4.500   0.8800   0.01144   0.00543  -0.0932   0.5904   1.0000
   4.750   0.9044   0.01165   0.00563  -0.0925   0.5716   1.0000
   5.000   0.9286   0.01189   0.00584  -0.0917   0.5522   1.0000
   5.250   0.9516   0.01210   0.00607  -0.0907   0.5297   1.0000
   5.500   0.9740   0.01235   0.00629  -0.0895   0.5054   1.0000
   5.750   0.9955   0.01263   0.00653  -0.0882   0.4780   1.0000
   6.000   1.0162   0.01295   0.00683  -0.0868   0.4465   1.0000
   6.250   1.0349   0.01337   0.00713  -0.0851   0.4064   1.0000
   6.500   1.0516   0.01393   0.00751  -0.0830   0.3550   1.0000
   6.750   1.0648   0.01477   0.00801  -0.0806   0.2901   1.0000
   7.000   1.0773   0.01580   0.00869  -0.0782   0.2263   1.0000
   7.250   1.0903   0.01688   0.00945  -0.0761   0.1736   1.0000
   7.500   1.1053   0.01785   0.01022  -0.0742   0.1349   1.0000
   7.750   1.1199   0.01886   0.01107  -0.0723   0.1014   1.0000
   8.000   1.1283   0.02040   0.01230  -0.0693   0.0585   1.0000
   8.250   1.1334   0.02204   0.01381  -0.0657   0.0383   1.0000
   8.500   1.1410   0.02339   0.01518  -0.0625   0.0324   1.0000
   8.750   1.1510   0.02455   0.01643  -0.0598   0.0293   1.0000
   9.000   1.1566   0.02609   0.01800  -0.0566   0.0274   1.0000
   9.250   1.1635   0.02780   0.01978  -0.0537   0.0262   1.0000
   9.500   1.1756   0.02921   0.02132  -0.0516   0.0252   1.0000
   9.750   1.1887   0.03080   0.02301  -0.0497   0.0243   1.0000
  10.000   1.2038   0.03252   0.02484  -0.0481   0.0236   1.0000
  10.250   1.2207   0.03439   0.02684  -0.0469   0.0230   1.0000
  10.500   1.2383   0.03645   0.02907  -0.0458   0.0225   1.0000
  10.750   1.2528   0.03840   0.03116  -0.0444   0.0218   1.0000
  11.000   1.2657   0.04047   0.03335  -0.0431   0.0212   1.0000
  11.250   1.2812   0.04393   0.03697  -0.0425   0.0203   1.0000
  11.500   1.2887   0.04777   0.04112  -0.0410   0.0201   1.0000
  11.750   1.2896   0.05094   0.04457  -0.0387   0.0201   1.0000
  12.000   1.2866   0.05391   0.04781  -0.0362   0.0201   1.0000
  12.250   1.2808   0.05685   0.05101  -0.0339   0.0202   1.0000
  12.500   1.2724   0.05990   0.05432  -0.0319   0.0203   1.0000
  12.750   1.2614   0.06325   0.05792  -0.0304   0.0204   1.0000
  13.000   1.2477   0.06694   0.06187  -0.0294   0.0206   1.0000
  13.250   1.2302   0.07133   0.06657  -0.0292   0.0208   1.0000
  13.500   1.2043   0.07736   0.07296  -0.0302   0.0213   1.0000
  13.750   1.1650   0.08586   0.08187  -0.0335   0.0219   1.0000
  14.000   1.1297   0.09516   0.09148  -0.0384   0.0225   1.0000
  14.250   1.0973   0.10512   0.10168  -0.0446   0.0229   1.0000
  14.500   1.0641   0.11673   0.11349  -0.0525   0.0233   1.0000
  14.750   1.0247   0.13222   0.12914  -0.0633   0.0240   1.0000
  15.000   0.9890   0.14964   0.14659  -0.0741   0.0254   1.0000
  15.250   0.9798   0.15794   0.15486  -0.0782   0.0263   1.0000
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