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E201 (11.88%) (e201-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: E201 (11.88%) (e201-il)
Reynolds number: 200,000
Max Cl/Cd: 80.37 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e201-il-200000.txt
Download as CSV file: xf-e201-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E201  (11.88%)                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4029   0.08811   0.08477  -0.0505   1.0000   0.0630
  -9.000  -0.4256   0.08236   0.07911  -0.0559   1.0000   0.0633
  -8.750  -0.4531   0.07870   0.07549  -0.0574   1.0000   0.0633
  -8.500  -0.4358   0.07497   0.07187  -0.0525   1.0000   0.0648
  -8.250  -0.4377   0.07334   0.07031  -0.0497   1.0000   0.0656
  -8.000  -0.4561   0.07043   0.06748  -0.0491   1.0000   0.0660
  -7.750  -0.4799   0.06782   0.06493  -0.0472   1.0000   0.0662
  -7.500  -0.4654   0.06391   0.06098  -0.0513   0.9954   0.0682
  -7.250  -0.4555   0.05267   0.04887  -0.0691   0.9792   0.0772
  -7.000  -0.4398   0.03534   0.03037  -0.0734   0.9717   0.0391
  -6.750  -0.4130   0.03120   0.02575  -0.0755   0.9620   0.0385
  -6.500  -0.3774   0.02724   0.02126  -0.0784   0.9576   0.0376
  -6.250  -0.3472   0.02420   0.01773  -0.0794   0.9481   0.0366
  -6.000  -0.3077   0.02172   0.01486  -0.0819   0.9441   0.0365
  -5.750  -0.2753   0.02002   0.01293  -0.0827   0.9345   0.0371
  -5.500  -0.2368   0.01848   0.01122  -0.0846   0.9293   0.0384
  -5.250  -0.2054   0.01748   0.01007  -0.0851   0.9183   0.0402
  -5.000  -0.1754   0.01607   0.00868  -0.0858   0.9082   0.0441
  -4.750  -0.1428   0.01518   0.00772  -0.0866   0.8991   0.0489
  -4.500  -0.1157   0.01421   0.00671  -0.0864   0.8869   0.0580
  -4.250  -0.0911   0.01299   0.00574  -0.0859   0.8743   0.1181
  -4.000  -0.0656   0.01228   0.00533  -0.0857   0.8623   0.1958
  -3.750  -0.0401   0.01175   0.00504  -0.0854   0.8512   0.2745
  -3.500  -0.0150   0.01130   0.00489  -0.0850   0.8408   0.3709
  -3.250   0.0094   0.01110   0.00484  -0.0843   0.8292   0.4469
  -3.000   0.0350   0.01099   0.00478  -0.0837   0.8189   0.4959
  -2.750   0.0616   0.01093   0.00468  -0.0832   0.8103   0.5355
  -2.500   0.0867   0.01085   0.00464  -0.0824   0.8000   0.5710
  -2.250   0.1124   0.01080   0.00460  -0.0818   0.7913   0.6056
  -2.000   0.1385   0.01075   0.00454  -0.0812   0.7830   0.6371
  -1.750   0.1638   0.01070   0.00452  -0.0805   0.7743   0.6679
  -1.500   0.1898   0.01065   0.00447  -0.0798   0.7670   0.6999
  -1.250   0.2144   0.01060   0.00450  -0.0789   0.7587   0.7332
  -1.000   0.2396   0.01054   0.00448  -0.0779   0.7520   0.7695
  -0.750   0.2630   0.01049   0.00452  -0.0767   0.7441   0.8102
  -0.500   0.2878   0.01045   0.00453  -0.0754   0.7376   0.8561
  -0.250   0.3176   0.01046   0.00459  -0.0752   0.7304   0.9046
   0.000   0.3606   0.01049   0.00455  -0.0780   0.7238   0.9463
   0.250   0.4108   0.01055   0.00453  -0.0826   0.7171   0.9767
   0.500   0.4662   0.01056   0.00445  -0.0886   0.7102   0.9978
   0.750   0.4907   0.01067   0.00446  -0.0884   0.7039   1.0000
   1.000   0.5122   0.01080   0.00453  -0.0874   0.6969   1.0000
   1.250   0.5366   0.01095   0.00457  -0.0868   0.6914   1.0000
   1.500   0.5589   0.01110   0.00472  -0.0859   0.6841   1.0000
   1.750   0.5840   0.01125   0.00480  -0.0854   0.6784   1.0000
   2.000   0.6079   0.01144   0.00497  -0.0848   0.6718   1.0000
   2.250   0.6329   0.01160   0.00510  -0.0843   0.6655   1.0000
   2.500   0.6587   0.01178   0.00525  -0.0839   0.6598   1.0000
   2.750   0.6832   0.01195   0.00544  -0.0833   0.6527   1.0000
   3.000   0.7102   0.01212   0.00554  -0.0831   0.6472   1.0000
   3.250   0.7342   0.01229   0.00578  -0.0824   0.6393   1.0000
   3.500   0.7611   0.01243   0.00586  -0.0822   0.6329   1.0000
   3.750   0.7854   0.01259   0.00609  -0.0815   0.6247   1.0000
   4.000   0.8125   0.01272   0.00618  -0.0813   0.6179   1.0000
   4.250   0.8365   0.01286   0.00640  -0.0805   0.6089   1.0000
   4.500   0.8632   0.01297   0.00648  -0.0802   0.6011   1.0000
   4.750   0.8877   0.01307   0.00666  -0.0795   0.5916   1.0000
   5.000   0.9128   0.01319   0.00682  -0.0789   0.5825   1.0000
   5.250   0.9391   0.01326   0.00687  -0.0785   0.5734   1.0000
   5.500   0.9628   0.01334   0.00705  -0.0776   0.5623   1.0000
   5.750   0.9872   0.01342   0.00721  -0.0768   0.5511   1.0000
   6.000   1.0117   0.01348   0.00732  -0.0761   0.5396   1.0000
   6.250   1.0357   0.01354   0.00742  -0.0752   0.5268   1.0000
   6.500   1.0585   0.01360   0.00755  -0.0741   0.5115   1.0000
   6.750   1.0806   0.01368   0.00772  -0.0729   0.4939   1.0000
   7.000   1.1021   0.01379   0.00787  -0.0717   0.4737   1.0000
   7.250   1.1219   0.01396   0.00805  -0.0701   0.4469   1.0000
   7.500   1.1387   0.01426   0.00827  -0.0680   0.4084   1.0000
   7.750   1.1509   0.01487   0.00866  -0.0654   0.3530   1.0000
   8.000   1.1581   0.01587   0.00930  -0.0621   0.2883   1.0000
   8.250   1.1631   0.01708   0.01017  -0.0588   0.2318   1.0000
   8.500   1.1682   0.01829   0.01113  -0.0556   0.1862   1.0000
   8.750   1.1724   0.01946   0.01209  -0.0522   0.1489   1.0000
   9.000   1.1736   0.02071   0.01315  -0.0485   0.1161   1.0000
   9.250   1.1725   0.02221   0.01441  -0.0448   0.0812   1.0000
   9.500   1.1658   0.02417   0.01613  -0.0407   0.0533   1.0000
   9.750   1.1609   0.02621   0.01813  -0.0371   0.0389   1.0000
  10.000   1.1566   0.02833   0.02026  -0.0341   0.0340   1.0000
  10.250   1.1596   0.03008   0.02212  -0.0320   0.0311   1.0000
  10.500   1.1622   0.03196   0.02408  -0.0302   0.0290   1.0000
  10.750   1.1636   0.03404   0.02622  -0.0285   0.0274   1.0000
  11.000   1.1617   0.03659   0.02879  -0.0267   0.0262   1.0000
  11.250   1.1680   0.03853   0.03081  -0.0253   0.0254   1.0000
  11.500   1.1765   0.04027   0.03268  -0.0243   0.0240   1.0000
  11.750   1.1854   0.04207   0.03457  -0.0232   0.0232   1.0000
  12.000   1.1936   0.04394   0.03651  -0.0223   0.0221   1.0000
  12.250   1.2034   0.04585   0.03852  -0.0212   0.0214   1.0000
  12.500   1.2148   0.04782   0.04052  -0.0202   0.0207   1.0000
  12.750   1.2303   0.04991   0.04269  -0.0191   0.0202   1.0000
  13.000   1.2481   0.05250   0.04544  -0.0180   0.0199   1.0000
  13.250   1.2606   0.05569   0.04887  -0.0171   0.0198   1.0000
  13.500   1.2640   0.05916   0.05258  -0.0163   0.0197   1.0000
  13.750   1.2643   0.06283   0.05649  -0.0157   0.0197   1.0000
  14.000   1.2606   0.06633   0.06024  -0.0154   0.0198   1.0000
  14.250   1.2539   0.07012   0.06426  -0.0153   0.0198   1.0000
  14.500   1.2452   0.07402   0.06839  -0.0155   0.0199   1.0000
  14.750   1.2345   0.07819   0.07278  -0.0162   0.0200   1.0000
  15.000   1.2205   0.08292   0.07776  -0.0174   0.0202   1.0000
  15.250   1.2033   0.08833   0.08344  -0.0192   0.0204   1.0000
  15.500   1.1795   0.09531   0.09076  -0.0221   0.0209   1.0000
  15.750   1.1461   0.10455   0.10034  -0.0269   0.0213   1.0000
  16.000   1.1091   0.11557   0.11170  -0.0335   0.0219   1.0000
  16.250   1.0738   0.12767   0.12406  -0.0412   0.0224   1.0000
  16.500   1.0351   0.14240   0.13899  -0.0511   0.0230   1.0000
  16.750   0.9890   0.16247   0.15918  -0.0637   0.0244   1.0000
  17.000   0.9754   0.17271   0.16937  -0.0691   0.0255   1.0000
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