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E201 (11.88%) (e201-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: E201 (11.88%) (e201-il)
Reynolds number: 200,000
Max Cl/Cd: 78.16 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e201-il-200000-n5.txt
Download as CSV file: xf-e201-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.4145   0.09007   0.08646  -0.0439   1.0000   0.0172
 -10.000  -0.4238   0.08442   0.08087  -0.0462   1.0000   0.0171
  -9.500  -0.5619   0.05040   0.04671  -0.0669   1.0000   0.0151
  -9.250  -0.5887   0.04692   0.04308  -0.0650   1.0000   0.0151
  -9.000  -0.5983   0.04250   0.03832  -0.0656   0.9966   0.0150
  -8.750  -0.5825   0.03776   0.03314  -0.0698   0.9874   0.0152
  -8.500  -0.5609   0.03456   0.02960  -0.0725   0.9793   0.0155
  -8.250  -0.5335   0.03265   0.02749  -0.0748   0.9723   0.0164
  -8.000  -0.5110   0.03007   0.02455  -0.0760   0.9621   0.0168
  -7.750  -0.4863   0.02746   0.02152  -0.0772   0.9525   0.0171
  -7.500  -0.4589   0.02514   0.01880  -0.0783   0.9434   0.0173
  -7.250  -0.4323   0.02331   0.01666  -0.0788   0.9320   0.0175
  -7.000  -0.4033   0.02171   0.01481  -0.0796   0.9212   0.0178
  -6.750  -0.3728   0.02033   0.01321  -0.0805   0.9105   0.0182
  -6.500  -0.3418   0.01911   0.01178  -0.0815   0.8992   0.0187
  -6.250  -0.3119   0.01809   0.01059  -0.0821   0.8863   0.0192
  -6.000  -0.2832   0.01721   0.00957  -0.0825   0.8725   0.0197
  -5.750  -0.2564   0.01629   0.00855  -0.0826   0.8582   0.0208
  -5.500  -0.2293   0.01572   0.00788  -0.0827   0.8441   0.0226
  -5.250  -0.2029   0.01519   0.00719  -0.0825   0.8303   0.0242
  -5.000  -0.1768   0.01470   0.00654  -0.0821   0.8171   0.0254
  -4.750  -0.1511   0.01419   0.00592  -0.0818   0.8046   0.0278
  -4.500  -0.1250   0.01379   0.00540  -0.0814   0.7930   0.0325
  -4.250  -0.0994   0.01332   0.00491  -0.0810   0.7821   0.0471
  -4.000  -0.0741   0.01287   0.00454  -0.0807   0.7712   0.0797
  -3.750  -0.0488   0.01244   0.00425  -0.0805   0.7613   0.1237
  -3.250   0.0021   0.01168   0.00377  -0.0800   0.7428   0.2325
  -3.000   0.0272   0.01130   0.00361  -0.0797   0.7346   0.3048
  -2.750   0.0525   0.01102   0.00352  -0.0793   0.7261   0.3764
  -2.500   0.0786   0.01087   0.00344  -0.0790   0.7185   0.4285
  -2.250   0.1048   0.01076   0.00337  -0.0786   0.7108   0.4703
  -2.000   0.1314   0.01068   0.00330  -0.0783   0.7038   0.5026
  -1.750   0.1580   0.01061   0.00324  -0.0780   0.6966   0.5315
  -1.500   0.1845   0.01055   0.00319  -0.0777   0.6902   0.5596
  -1.250   0.2110   0.01049   0.00316  -0.0773   0.6832   0.5872
  -1.000   0.2375   0.01045   0.00312  -0.0769   0.6774   0.6154
  -0.750   0.2638   0.01039   0.00312  -0.0765   0.6706   0.6449
  -0.500   0.2898   0.01034   0.00312  -0.0760   0.6647   0.6766
  -0.250   0.3156   0.01028   0.00314  -0.0755   0.6588   0.7103
   0.000   0.3411   0.01023   0.00317  -0.0748   0.6527   0.7471
   0.250   0.3662   0.01019   0.00320  -0.0739   0.6476   0.7883
   0.500   0.3918   0.01013   0.00326  -0.0731   0.6413   0.8354
   0.750   0.4218   0.01012   0.00330  -0.0732   0.6358   0.8853
   1.000   0.4594   0.01014   0.00333  -0.0751   0.6302   0.9306
   1.250   0.4990   0.01018   0.00336  -0.0776   0.6241   0.9670
   1.500   0.5385   0.01026   0.00335  -0.0801   0.6189   0.9936
   1.750   0.5674   0.01035   0.00344  -0.0805   0.6128   1.0000
   2.000   0.5923   0.01046   0.00352  -0.0800   0.6073   1.0000
   2.250   0.6176   0.01059   0.00360  -0.0796   0.6021   1.0000
   2.500   0.6428   0.01071   0.00372  -0.0791   0.5960   1.0000
   2.750   0.6685   0.01084   0.00382  -0.0787   0.5907   1.0000
   3.000   0.6941   0.01097   0.00397  -0.0783   0.5846   1.0000
   3.250   0.7197   0.01110   0.00410  -0.0779   0.5780   1.0000
   3.500   0.7453   0.01123   0.00423  -0.0775   0.5713   1.0000
   3.750   0.7707   0.01136   0.00438  -0.0771   0.5634   1.0000
   4.000   0.7962   0.01149   0.00454  -0.0766   0.5556   1.0000
   4.250   0.8215   0.01163   0.00468  -0.0762   0.5470   1.0000
   4.500   0.8466   0.01176   0.00486  -0.0757   0.5373   1.0000
   4.750   0.8716   0.01190   0.00503  -0.0751   0.5274   1.0000
   5.000   0.8964   0.01205   0.00520  -0.0745   0.5171   1.0000
   5.250   0.9210   0.01220   0.00540  -0.0739   0.5054   1.0000
   5.500   0.9453   0.01237   0.00560  -0.0733   0.4926   1.0000
   5.750   0.9692   0.01255   0.00583  -0.0726   0.4782   1.0000
   6.000   0.9926   0.01275   0.00606  -0.0717   0.4622   1.0000
   6.250   1.0153   0.01299   0.00630  -0.0708   0.4441   1.0000
   6.500   1.0372   0.01327   0.00658  -0.0698   0.4204   1.0000
   6.750   1.0569   0.01365   0.00690  -0.0684   0.3888   1.0000
   7.000   1.0726   0.01425   0.00729  -0.0664   0.3413   1.0000
   7.250   1.0836   0.01516   0.00789  -0.0638   0.2814   1.0000
   7.500   1.0923   0.01627   0.00866  -0.0611   0.2241   1.0000
   7.750   1.1016   0.01735   0.00948  -0.0585   0.1773   1.0000
   8.000   1.1120   0.01835   0.01028  -0.0561   0.1423   1.0000
   8.250   1.1223   0.01930   0.01111  -0.0537   0.1138   1.0000
   8.500   1.1300   0.02025   0.01194  -0.0508   0.0898   1.0000
   8.750   1.1367   0.02126   0.01284  -0.0480   0.0686   1.0000
   9.000   1.1443   0.02229   0.01380  -0.0453   0.0517   1.0000
   9.250   1.1497   0.02349   0.01491  -0.0427   0.0363   1.0000
   9.500   1.1550   0.02476   0.01615  -0.0401   0.0251   1.0000
   9.750   1.1614   0.02603   0.01744  -0.0379   0.0202   1.0000
  10.000   1.1678   0.02738   0.01885  -0.0359   0.0170   1.0000
  10.250   1.1738   0.02883   0.02038  -0.0340   0.0156   1.0000
  10.500   1.1806   0.03029   0.02195  -0.0324   0.0146   1.0000
  10.750   1.1869   0.03185   0.02363  -0.0310   0.0138   1.0000
  11.000   1.1918   0.03361   0.02550  -0.0296   0.0131   1.0000
  11.250   1.1962   0.03547   0.02746  -0.0284   0.0126   1.0000
  11.500   1.1983   0.03763   0.02972  -0.0273   0.0121   1.0000
  11.750   1.2005   0.03984   0.03204  -0.0264   0.0116   1.0000
  12.000   1.2039   0.04203   0.03436  -0.0256   0.0112   1.0000
  12.250   1.2069   0.04431   0.03676  -0.0250   0.0109   1.0000
  12.500   1.2097   0.04666   0.03926  -0.0244   0.0103   1.0000
  12.750   1.2117   0.04918   0.04188  -0.0240   0.0101   1.0000
  13.000   1.2126   0.05186   0.04468  -0.0237   0.0099   1.0000
  13.250   1.2135   0.05462   0.04756  -0.0235   0.0097   1.0000
  13.500   1.2139   0.05750   0.05056  -0.0234   0.0095   1.0000
  13.750   1.2140   0.06051   0.05368  -0.0235   0.0093   1.0000
  14.000   1.2143   0.06357   0.05684  -0.0236   0.0092   1.0000
  14.250   1.2140   0.06680   0.06019  -0.0239   0.0091   1.0000
  14.500   1.2132   0.07015   0.06365  -0.0242   0.0090   1.0000
  14.750   1.2127   0.07356   0.06719  -0.0247   0.0089   1.0000
  15.000   1.2114   0.07718   0.07093  -0.0253   0.0088   1.0000
  15.250   1.2097   0.08095   0.07483  -0.0259   0.0087   1.0000
  15.500   1.2064   0.08508   0.07912  -0.0269   0.0085   1.0000
  15.750   1.2035   0.08928   0.08351  -0.0281   0.0085   1.0000
  16.000   1.1993   0.09380   0.08821  -0.0296   0.0085   1.0000
  16.250   1.1945   0.09853   0.09311  -0.0314   0.0085   1.0000
  16.500   1.1867   0.10398   0.09877  -0.0337   0.0084   1.0000
  16.750   1.1792   0.10948   0.10445  -0.0362   0.0084   1.0000
  17.000   1.1704   0.11544   0.11060  -0.0392   0.0084   1.0000
  17.250   1.1602   0.12187   0.11722  -0.0426   0.0084   1.0000
  17.500   1.1483   0.12892   0.12446  -0.0466   0.0084   1.0000
  17.750   1.1366   0.13616   0.13188  -0.0509   0.0084   1.0000
  18.000   1.1237   0.14400   0.13990  -0.0557   0.0084   1.0000
  18.250   1.1106   0.15225   0.14831  -0.0609   0.0085   1.0000
  18.500   1.0956   0.16142   0.15764  -0.0668   0.0085   1.0000
  18.750   1.0805   0.17100   0.16736  -0.0729   0.0086   1.0000
  19.000   1.0583   0.18404   0.18057  -0.0811   0.0087   1.0000
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