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E216 (10.4%) (e216-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: E216 (10.4%) (e216-il)
Reynolds number: 200,000
Max Cl/Cd: 94.03 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e216-il-200000-n5.txt
Download as CSV file: xf-e216-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E216  (10.4%)                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.2561   0.07702   0.07352  -0.0717   0.9636   0.0156
  -7.000  -0.2598   0.04179   0.03785  -0.1160   0.9420   0.0143
  -6.750  -0.2279   0.03288   0.02800  -0.1299   0.9355   0.0144
  -6.500  -0.1885   0.02838   0.02281  -0.1369   0.9333   0.0145
  -6.250  -0.1491   0.02547   0.01936  -0.1416   0.9318   0.0146
  -6.000  -0.1108   0.02324   0.01678  -0.1452   0.9305   0.0149
  -5.750  -0.0730   0.02164   0.01497  -0.1482   0.9293   0.0153
  -5.500  -0.0350   0.02040   0.01355  -0.1510   0.9282   0.0159
  -5.250  -0.0084   0.01952   0.01255  -0.1513   0.9227   0.0165
  -5.000   0.0267   0.01861   0.01150  -0.1532   0.9199   0.0173
  -4.750   0.0634   0.01785   0.01060  -0.1553   0.9178   0.0187
  -4.500   0.1013   0.01711   0.00981  -0.1578   0.9161   0.0211
  -4.250   0.1403   0.01641   0.00896  -0.1603   0.9147   0.0232
  -4.000   0.1708   0.01590   0.00840  -0.1612   0.9098   0.0264
  -3.750   0.2053   0.01535   0.00781  -0.1627   0.9061   0.0356
  -3.500   0.2429   0.01468   0.00730  -0.1650   0.9037   0.0710
  -3.250   0.2805   0.01414   0.00690  -0.1673   0.9017   0.1148
  -3.000   0.3190   0.01360   0.00657  -0.1698   0.9001   0.1755
  -2.750   0.3462   0.01341   0.00644  -0.1698   0.8931   0.2112
  -2.500   0.3809   0.01310   0.00617  -0.1712   0.8893   0.2482
  -2.250   0.4184   0.01274   0.00589  -0.1732   0.8866   0.2890
  -2.000   0.4498   0.01254   0.00574  -0.1739   0.8809   0.3251
  -1.750   0.4827   0.01232   0.00557  -0.1748   0.8753   0.3589
  -1.500   0.5209   0.01202   0.00531  -0.1769   0.8717   0.3939
  -1.250   0.5519   0.01189   0.00522  -0.1774   0.8644   0.4256
  -1.000   0.5882   0.01166   0.00505  -0.1790   0.8587   0.4584
  -0.750   0.6252   0.01146   0.00489  -0.1808   0.8526   0.4902
  -0.500   0.6593   0.01132   0.00480  -0.1820   0.8445   0.5197
  -0.250   0.6966   0.01117   0.00469  -0.1838   0.8370   0.5496
   0.000   0.7324   0.01105   0.00461  -0.1853   0.8281   0.5784
   0.250   0.7654   0.01097   0.00457  -0.1862   0.8178   0.6061
   0.500   0.8007   0.01089   0.00451  -0.1875   0.8074   0.6343
   0.750   0.8342   0.01083   0.00448  -0.1885   0.7956   0.6613
   1.000   0.8644   0.01083   0.00450  -0.1888   0.7821   0.6872
   1.250   0.8943   0.01084   0.00454  -0.1889   0.7678   0.7135
   1.500   0.9228   0.01088   0.00458  -0.1888   0.7527   0.7388
   1.750   0.9503   0.01094   0.00464  -0.1885   0.7367   0.7644
   2.000   0.9765   0.01103   0.00471  -0.1879   0.7201   0.7908
   2.250   1.0008   0.01113   0.00481  -0.1869   0.7031   0.8177
   2.500   1.0229   0.01123   0.00490  -0.1854   0.6856   0.8466
   2.750   1.0430   0.01132   0.00498  -0.1835   0.6678   0.8802
   3.250   1.0842   0.01153   0.00511  -0.1801   0.6300   1.0000
   3.500   1.1098   0.01182   0.00530  -0.1796   0.6095   1.0000
   3.750   1.1344   0.01212   0.00552  -0.1790   0.5882   1.0000
   4.000   1.1585   0.01245   0.00577  -0.1782   0.5671   1.0000
   4.250   1.1818   0.01280   0.00604  -0.1773   0.5461   1.0000
   4.500   1.2046   0.01316   0.00633  -0.1763   0.5241   1.0000
   4.750   1.2264   0.01357   0.00665  -0.1752   0.5017   1.0000
   5.000   1.2478   0.01398   0.00699  -0.1739   0.4781   1.0000
   5.500   1.2885   0.01489   0.00775  -0.1711   0.4314   1.0000
   5.750   1.3077   0.01539   0.00818  -0.1695   0.4086   1.0000
   6.000   1.3265   0.01589   0.00862  -0.1679   0.3851   1.0000
   6.500   1.3614   0.01701   0.00961  -0.1642   0.3378   1.0000
   6.750   1.3777   0.01765   0.01018  -0.1621   0.3134   1.0000
   7.000   1.3938   0.01832   0.01077  -0.1601   0.2885   1.0000
   7.250   1.4095   0.01903   0.01141  -0.1581   0.2644   1.0000
   7.500   1.4239   0.01984   0.01212  -0.1559   0.2392   1.0000
   7.750   1.4381   0.02068   0.01288  -0.1538   0.2133   1.0000
   8.000   1.4512   0.02160   0.01370  -0.1515   0.1867   1.0000
   8.250   1.4636   0.02261   0.01459  -0.1492   0.1608   1.0000
   8.500   1.4754   0.02368   0.01554  -0.1469   0.1374   1.0000
   8.750   1.4874   0.02476   0.01654  -0.1446   0.1159   1.0000
   9.000   1.4986   0.02590   0.01762  -0.1423   0.0977   1.0000
   9.250   1.5102   0.02704   0.01873  -0.1401   0.0822   1.0000
   9.500   1.5215   0.02820   0.01988  -0.1380   0.0697   1.0000
   9.750   1.5318   0.02946   0.02114  -0.1357   0.0577   1.0000
  10.000   1.5406   0.03086   0.02253  -0.1334   0.0461   1.0000
  10.250   1.5477   0.03244   0.02408  -0.1310   0.0356   1.0000
  10.500   1.5537   0.03415   0.02581  -0.1285   0.0275   1.0000
  10.750   1.5599   0.03587   0.02759  -0.1262   0.0223   1.0000
  11.000   1.5662   0.03762   0.02945  -0.1239   0.0195   1.0000
  11.250   1.5712   0.03954   0.03146  -0.1218   0.0178   1.0000
  11.500   1.5753   0.04159   0.03362  -0.1197   0.0166   1.0000
  11.750   1.5795   0.04368   0.03588  -0.1177   0.0157   1.0000
  12.000   1.5825   0.04595   0.03829  -0.1159   0.0151   1.0000
  12.250   1.5843   0.04842   0.04092  -0.1142   0.0145   1.0000
  12.500   1.5842   0.05118   0.04382  -0.1127   0.0140   1.0000
  12.750   1.5816   0.05432   0.04709  -0.1113   0.0136   1.0000
  13.000   1.5804   0.05744   0.05037  -0.1101   0.0132   1.0000
  13.250   1.5790   0.06071   0.05382  -0.1093   0.0129   1.0000
  13.500   1.5772   0.06417   0.05744  -0.1087   0.0125   1.0000
  13.750   1.5743   0.06788   0.06132  -0.1083   0.0121   1.0000
  14.000   1.5709   0.07181   0.06540  -0.1082   0.0118   1.0000
  14.250   1.5670   0.07596   0.06971  -0.1084   0.0116   1.0000
  14.500   1.5619   0.08040   0.07431  -0.1089   0.0114   1.0000
  14.750   1.5564   0.08504   0.07910  -0.1096   0.0112   1.0000
  15.000   1.5508   0.08983   0.08406  -0.1105   0.0111   1.0000
  15.250   1.5446   0.09482   0.08919  -0.1118   0.0109   1.0000
  15.500   1.5386   0.09989   0.09440  -0.1132   0.0108   1.0000
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