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E201 (11.88%) (e201-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: E201 (11.88%) (e201-il)
Reynolds number: 100,000
Max Cl/Cd: 57.01 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e201-il-100000-n5.txt
Download as CSV file: xf-e201-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4001   0.08970   0.08470  -0.0454   1.0000   0.0295
  -9.500  -0.4076   0.08466   0.07973  -0.0474   1.0000   0.0289
  -9.250  -0.4205   0.07865   0.07382  -0.0501   1.0000   0.0282
  -9.000  -0.4849   0.06204   0.05726  -0.0619   1.0000   0.0263
  -8.750  -0.5219   0.05701   0.05210  -0.0624   1.0000   0.0258
  -8.500  -0.5395   0.05367   0.04859  -0.0610   1.0000   0.0257
  -8.250  -0.5525   0.05058   0.04535  -0.0590   1.0000   0.0256
  -8.000  -0.5543   0.04699   0.04150  -0.0588   0.9972   0.0255
  -7.750  -0.5337   0.04188   0.03580  -0.0630   0.9872   0.0255
  -7.500  -0.5100   0.03769   0.03103  -0.0659   0.9773   0.0256
  -7.250  -0.4833   0.03417   0.02704  -0.0683   0.9685   0.0259
  -7.000  -0.4551   0.03140   0.02392  -0.0701   0.9595   0.0263
  -6.750  -0.4264   0.02923   0.02146  -0.0714   0.9499   0.0269
  -6.500  -0.3925   0.02757   0.01958  -0.0735   0.9429   0.0286
  -6.250  -0.3629   0.02607   0.01780  -0.0744   0.9326   0.0305
  -6.000  -0.3320   0.02451   0.01597  -0.0752   0.9232   0.0320
  -5.750  -0.2989   0.02305   0.01428  -0.0764   0.9152   0.0331
  -5.500  -0.2709   0.02170   0.01289  -0.0768   0.9043   0.0347
  -5.250  -0.2407   0.02067   0.01175  -0.0775   0.8944   0.0371
  -5.000  -0.2088   0.01972   0.01062  -0.0784   0.8856   0.0409
  -4.750  -0.1808   0.01885   0.00970  -0.0786   0.8742   0.0484
  -4.500  -0.1521   0.01796   0.00878  -0.0790   0.8637   0.0655
  -4.250  -0.1227   0.01707   0.00800  -0.0795   0.8543   0.1022
  -4.000  -0.0959   0.01632   0.00752  -0.0797   0.8435   0.1678
  -3.750  -0.0700   0.01561   0.00716  -0.0798   0.8329   0.2530
  -3.500  -0.0427   0.01511   0.00686  -0.0798   0.8236   0.3254
  -3.250  -0.0162   0.01480   0.00667  -0.0795   0.8136   0.3947
  -3.000   0.0101   0.01460   0.00652  -0.0791   0.8039   0.4517
  -2.750   0.0378   0.01444   0.00635  -0.0788   0.7957   0.4991
  -2.500   0.0637   0.01433   0.00624  -0.0782   0.7860   0.5382
  -2.250   0.0904   0.01422   0.00611  -0.0777   0.7777   0.5739
  -2.000   0.1169   0.01413   0.00601  -0.0772   0.7694   0.6081
  -1.750   0.1430   0.01406   0.00593  -0.0766   0.7612   0.6416
  -1.500   0.1694   0.01398   0.00584  -0.0760   0.7537   0.6750
  -1.250   0.1947   0.01392   0.00581  -0.0751   0.7458   0.7096
  -1.000   0.2207   0.01386   0.00576  -0.0743   0.7388   0.7467
  -0.750   0.2458   0.01382   0.00576  -0.0734   0.7313   0.7857
  -0.500   0.2733   0.01377   0.00573  -0.0727   0.7245   0.8290
  -0.250   0.3054   0.01376   0.00572  -0.0731   0.7176   0.8760
   0.000   0.3461   0.01376   0.00567  -0.0755   0.7108   0.9220
   0.250   0.3902   0.01379   0.00560  -0.0788   0.7044   0.9623
   0.500   0.4349   0.01383   0.00555  -0.0826   0.6973   0.9962
   0.750   0.4610   0.01395   0.00555  -0.0825   0.6914   1.0000
   1.000   0.4834   0.01412   0.00566  -0.0817   0.6840   1.0000
   1.250   0.5084   0.01426   0.00570  -0.0812   0.6784   1.0000
   1.500   0.5316   0.01446   0.00587  -0.0806   0.6713   1.0000
   1.750   0.5568   0.01463   0.00597  -0.0801   0.6653   1.0000
   2.000   0.5814   0.01483   0.00613  -0.0796   0.6590   1.0000
   2.250   0.6062   0.01503   0.00632  -0.0791   0.6525   1.0000
   2.500   0.6324   0.01521   0.00646  -0.0788   0.6471   1.0000
   2.750   0.6563   0.01545   0.00673  -0.0782   0.6400   1.0000
   3.000   0.6828   0.01564   0.00690  -0.0780   0.6344   1.0000
   3.250   0.7069   0.01589   0.00720  -0.0774   0.6274   1.0000
   3.500   0.7327   0.01609   0.00741  -0.0770   0.6212   1.0000
   3.750   0.7575   0.01633   0.00769  -0.0765   0.6143   1.0000
   4.000   0.7827   0.01654   0.00796  -0.0761   0.6070   1.0000
   4.250   0.8075   0.01676   0.00823  -0.0755   0.5994   1.0000
   4.500   0.8328   0.01694   0.00846  -0.0750   0.5914   1.0000
   4.750   0.8566   0.01717   0.00876  -0.0743   0.5824   1.0000
   5.000   0.8829   0.01729   0.00893  -0.0738   0.5742   1.0000
   5.250   0.9056   0.01750   0.00926  -0.0729   0.5632   1.0000
   5.500   0.9290   0.01768   0.00953  -0.0720   0.5522   1.0000
   5.750   0.9529   0.01783   0.00975  -0.0712   0.5409   1.0000
   6.000   0.9766   0.01796   0.00999  -0.0703   0.5289   1.0000
   6.250   0.9993   0.01811   0.01023  -0.0693   0.5151   1.0000
   6.500   1.0209   0.01829   0.01052  -0.0681   0.4993   1.0000
   6.750   1.0418   0.01850   0.01084  -0.0668   0.4817   1.0000
   7.000   1.0623   0.01871   0.01116  -0.0654   0.4619   1.0000
   7.250   1.0815   0.01897   0.01150  -0.0638   0.4389   1.0000
   7.500   1.0992   0.01931   0.01186  -0.0620   0.4105   1.0000
   7.750   1.1146   0.01977   0.01228  -0.0598   0.3750   1.0000
   8.000   1.1265   0.02045   0.01281  -0.0573   0.3316   1.0000
   8.250   1.1340   0.02141   0.01357  -0.0543   0.2855   1.0000
   8.500   1.1377   0.02264   0.01453  -0.0510   0.2402   1.0000
   8.750   1.1381   0.02399   0.01565  -0.0473   0.2003   1.0000
   9.000   1.1363   0.02547   0.01689  -0.0437   0.1624   1.0000
   9.250   1.1347   0.02710   0.01828  -0.0404   0.1288   1.0000
   9.500   1.1343   0.02879   0.01976  -0.0376   0.0994   1.0000
   9.750   1.1358   0.03047   0.02133  -0.0353   0.0799   1.0000
  10.000   1.1382   0.03221   0.02303  -0.0332   0.0626   1.0000
  10.250   1.1401   0.03410   0.02491  -0.0314   0.0504   1.0000
  10.750   1.1391   0.03862   0.02945  -0.0280   0.0355   1.0000
  11.000   1.1403   0.04091   0.03187  -0.0267   0.0307   1.0000
  11.250   1.1400   0.04340   0.03443  -0.0257   0.0281   1.0000
  11.500   1.1403   0.04594   0.03706  -0.0248   0.0259   1.0000
  11.750   1.1425   0.04835   0.03962  -0.0241   0.0239   1.0000
  12.000   1.1437   0.05094   0.04232  -0.0235   0.0224   1.0000
  12.250   1.1440   0.05369   0.04517  -0.0231   0.0215   1.0000
  12.500   1.1420   0.05675   0.04832  -0.0227   0.0207   1.0000
  12.750   1.1445   0.05943   0.05114  -0.0222   0.0202   1.0000
  13.000   1.1474   0.06213   0.05400  -0.0218   0.0196   1.0000
  13.250   1.1506   0.06486   0.05693  -0.0215   0.0191   1.0000
  13.500   1.1538   0.06771   0.05994  -0.0212   0.0185   1.0000
  13.750   1.1567   0.07067   0.06306  -0.0211   0.0181   1.0000
  14.000   1.1588   0.07378   0.06634  -0.0211   0.0177   1.0000
  14.250   1.1599   0.07714   0.06987  -0.0214   0.0174   1.0000
  14.500   1.1592   0.08077   0.07368  -0.0219   0.0171   1.0000
  14.750   1.1572   0.08467   0.07775  -0.0227   0.0168   1.0000
  15.000   1.1537   0.08884   0.08208  -0.0239   0.0165   1.0000
  15.250   1.1493   0.09328   0.08668  -0.0253   0.0163   1.0000
  15.500   1.1441   0.09782   0.09131  -0.0269   0.0159   1.0000
  15.750   1.1352   0.10333   0.09702  -0.0292   0.0157   1.0000
  16.000   1.1241   0.10947   0.10341  -0.0321   0.0157   1.0000
  16.250   1.1130   0.11585   0.11000  -0.0354   0.0157   1.0000
  16.500   1.0971   0.12356   0.11796  -0.0399   0.0156   1.0000
  16.750   1.0845   0.13087   0.12545  -0.0441   0.0157   1.0000
  17.000   1.0697   0.13910   0.13386  -0.0493   0.0157   1.0000
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