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E216 (10.4%) (e216-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: E216 (10.4%) (e216-il)
Reynolds number: 1,000,000
Max Cl/Cd: 155.1 at α=1.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e216-il-1000000.txt
Download as CSV file: xf-e216-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2318   0.10024   0.09851  -0.0715   0.9859   0.0126
  -9.500  -0.2288   0.09638   0.09466  -0.0727   0.9818   0.0126
  -9.250  -0.2268   0.09033   0.08863  -0.0768   0.9796   0.0128
  -9.000  -0.2131   0.08764   0.08594  -0.0795   0.9784   0.0131
  -8.750  -0.1983   0.08446   0.08275  -0.0830   0.9773   0.0133
  -8.500  -0.1830   0.08092   0.07921  -0.0871   0.9764   0.0137
  -8.250  -0.1676   0.07687   0.07517  -0.0920   0.9756   0.0140
  -7.500  -0.1549   0.01946   0.01584  -0.1660   0.9529   0.0097
  -7.250  -0.1337   0.01802   0.01420  -0.1658   0.9474   0.0097
  -7.000  -0.0978   0.01540   0.01125  -0.1693   0.9462   0.0098
  -6.750  -0.0624   0.01391   0.00964  -0.1719   0.9452   0.0103
  -6.500  -0.0271   0.01305   0.00869  -0.1739   0.9443   0.0107
  -6.250   0.0085   0.01225   0.00781  -0.1760   0.9435   0.0111
  -6.000   0.0444   0.01151   0.00699  -0.1780   0.9427   0.0114
  -5.750   0.0805   0.01082   0.00622  -0.1800   0.9421   0.0117
  -5.500   0.1172   0.01019   0.00553  -0.1821   0.9414   0.0121
  -5.250   0.1543   0.00965   0.00492  -0.1842   0.9407   0.0124
  -5.000   0.1924   0.00904   0.00424  -0.1866   0.9400   0.0130
  -4.750   0.2173   0.00859   0.00374  -0.1861   0.9342   0.0139
  -4.500   0.2524   0.00818   0.00330  -0.1877   0.9317   0.0150
  -4.250   0.2888   0.00785   0.00291  -0.1895   0.9296   0.0163
  -4.000   0.3289   0.00744   0.00248  -0.1922   0.9280   0.0204
  -3.750   0.3723   0.00690   0.00213  -0.1959   0.9266   0.0657
  -3.500   0.3989   0.00666   0.00198  -0.1957   0.9194   0.0962
  -3.250   0.4389   0.00638   0.00181  -0.1985   0.9159   0.1366
  -3.000   0.4821   0.00613   0.00166  -0.2021   0.9127   0.1775
  -2.750   0.5118   0.00596   0.00158  -0.2025   0.9045   0.2151
  -2.500   0.5506   0.00578   0.00148  -0.2050   0.8988   0.2584
  -2.250   0.5807   0.00569   0.00143  -0.2055   0.8897   0.2884
  -2.000   0.6143   0.00561   0.00137  -0.2068   0.8814   0.3184
  -1.750   0.6451   0.00555   0.00134  -0.2074   0.8713   0.3501
  -1.500   0.6746   0.00551   0.00133  -0.2077   0.8604   0.3769
  -1.250   0.7039   0.00551   0.00132  -0.2080   0.8488   0.4011
  -1.000   0.7325   0.00552   0.00133  -0.2081   0.8363   0.4265
  -0.750   0.7602   0.00555   0.00134  -0.2080   0.8228   0.4500
  -0.500   0.7872   0.00559   0.00137  -0.2077   0.8084   0.4749
  -0.250   0.8137   0.00565   0.00141  -0.2074   0.7935   0.4982
   0.000   0.8399   0.00572   0.00147  -0.2069   0.7779   0.5216
   0.250   0.8657   0.00580   0.00153  -0.2064   0.7619   0.5437
   0.500   0.8914   0.00589   0.00160  -0.2059   0.7454   0.5658
   0.750   0.9167   0.00600   0.00168  -0.2053   0.7281   0.5879
   1.000   0.9419   0.00611   0.00177  -0.2047   0.7102   0.6098
   1.250   0.9665   0.00625   0.00188  -0.2039   0.6915   0.6323
   1.500   0.9911   0.00640   0.00199  -0.2032   0.6723   0.6541
   1.750   1.0159   0.00655   0.00211  -0.2025   0.6524   0.6764
   2.250   1.0647   0.00689   0.00239  -0.2010   0.6134   0.7206
   2.500   1.0893   0.00706   0.00254  -0.2002   0.5939   0.7432
   2.750   1.1135   0.00725   0.00270  -0.1995   0.5728   0.7652
   3.000   1.1370   0.00747   0.00288  -0.1985   0.5511   0.7879
   3.250   1.1608   0.00768   0.00305  -0.1977   0.5286   0.8109
   3.500   1.1839   0.00792   0.00324  -0.1967   0.5063   0.8347
   3.750   1.2068   0.00813   0.00343  -0.1956   0.4847   0.8590
   4.000   1.2285   0.00836   0.00364  -0.1943   0.4626   0.8858
   4.250   1.2480   0.00856   0.00381  -0.1925   0.4420   0.9196
   4.500   1.2654   0.00871   0.00394  -0.1902   0.4205   1.0000
   4.750   1.2891   0.00905   0.00417  -0.1895   0.3973   1.0000
   5.000   1.3120   0.00945   0.00444  -0.1886   0.3695   1.0000
   5.250   1.3339   0.00991   0.00474  -0.1875   0.3372   1.0000
   5.500   1.3553   0.01039   0.00505  -0.1864   0.3049   1.0000
   5.750   1.3765   0.01086   0.00539  -0.1852   0.2768   1.0000
   6.000   1.3979   0.01130   0.00571  -0.1841   0.2520   1.0000
   6.250   1.4183   0.01180   0.00608  -0.1828   0.2256   1.0000
   6.500   1.4377   0.01236   0.00649  -0.1813   0.1975   1.0000
   6.750   1.4568   0.01293   0.00692  -0.1797   0.1729   1.0000
   7.000   1.4754   0.01350   0.00737  -0.1781   0.1496   1.0000
   7.250   1.4940   0.01406   0.00783  -0.1765   0.1292   1.0000
   7.500   1.5113   0.01472   0.00835  -0.1746   0.1076   1.0000
   7.750   1.5291   0.01533   0.00887  -0.1729   0.0897   1.0000
   8.000   1.5459   0.01599   0.00944  -0.1710   0.0734   1.0000
   8.250   1.5615   0.01672   0.01007  -0.1689   0.0574   1.0000
   8.500   1.5762   0.01752   0.01077  -0.1667   0.0414   1.0000
   8.750   1.5876   0.01858   0.01169  -0.1640   0.0230   1.0000
   9.000   1.5996   0.01957   0.01262  -0.1613   0.0135   1.0000
   9.250   1.6143   0.02036   0.01343  -0.1591   0.0114   1.0000
   9.500   1.6297   0.02110   0.01422  -0.1571   0.0105   1.0000
   9.750   1.6449   0.02183   0.01501  -0.1551   0.0100   1.0000
  10.000   1.6593   0.02264   0.01588  -0.1530   0.0095   1.0000
  10.250   1.6722   0.02355   0.01684  -0.1508   0.0090   1.0000
  10.500   1.6835   0.02461   0.01798  -0.1483   0.0086   1.0000
  10.750   1.6917   0.02590   0.01937  -0.1455   0.0082   1.0000
  11.000   1.7008   0.02714   0.02070  -0.1429   0.0080   1.0000
  11.250   1.7119   0.02824   0.02187  -0.1407   0.0079   1.0000
  11.500   1.7216   0.02944   0.02316  -0.1384   0.0077   1.0000
  11.750   1.7309   0.03070   0.02450  -0.1362   0.0075   1.0000
  12.000   1.7389   0.03211   0.02599  -0.1339   0.0073   1.0000
  12.250   1.7457   0.03366   0.02763  -0.1316   0.0071   1.0000
  12.500   1.7510   0.03538   0.02944  -0.1293   0.0069   1.0000
  12.750   1.7553   0.03724   0.03139  -0.1270   0.0068   1.0000
  13.000   1.7583   0.03929   0.03354  -0.1248   0.0066   1.0000
  13.250   1.7600   0.04154   0.03589  -0.1228   0.0065   1.0000
  13.500   1.7587   0.04420   0.03866  -0.1207   0.0064   1.0000
  13.750   1.7570   0.04704   0.04160  -0.1189   0.0063   1.0000
  14.000   1.7519   0.05041   0.04510  -0.1172   0.0062   1.0000
  14.250   1.7433   0.05438   0.04920  -0.1157   0.0061   1.0000
  14.500   1.7324   0.05888   0.05385  -0.1146   0.0060   1.0000
  14.750   1.7215   0.06365   0.05876  -0.1140   0.0059   1.0000
  15.250   1.7090   0.07243   0.06781  -0.1138   0.0058   1.0000
  15.500   1.7049   0.07675   0.07225  -0.1141   0.0058   1.0000
  15.750   1.7022   0.08098   0.07660  -0.1147   0.0058   1.0000
  16.000   1.6961   0.08587   0.08161  -0.1156   0.0057   1.0000
  16.250   1.6893   0.09100   0.08687  -0.1167   0.0057   1.0000
  16.500   1.6832   0.09615   0.09215  -0.1181   0.0057   1.0000
  16.750   1.6778   0.10130   0.09743  -0.1198   0.0056   1.0000
  17.000   1.6697   0.10700   0.10326  -0.1217   0.0056   1.0000
  17.250   1.6622   0.11269   0.10908  -0.1239   0.0055   1.0000
  17.500   1.6555   0.11832   0.11483  -0.1263   0.0055   1.0000
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