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E216 (10.4%) (e216-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: E216 (10.4%) (e216-il)
Reynolds number: 50,000
Max Cl/Cd: 40.73 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e216-il-50000.txt
Download as CSV file: xf-e216-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.000  -0.3770   0.11401   0.10794  -0.0191   1.0000   0.2104
  -6.750  -0.3553   0.10872   0.10262  -0.0173   1.0000   0.2192
  -6.500  -0.3776   0.10881   0.10286  -0.0151   1.0000   0.2249
  -6.250  -0.4090   0.10966   0.10390  -0.0135   1.0000   0.2264
  -6.000  -0.3812   0.10398   0.09817  -0.0109   1.0000   0.2379
  -5.750  -0.4124   0.10472   0.09909  -0.0106   1.0000   0.2417
  -5.500  -0.3936   0.09999   0.09436  -0.0068   1.0000   0.2502
  -5.250  -0.4212   0.10036   0.09491  -0.0102   1.0000   0.2577
  -5.000  -0.4038   0.09577   0.09030  -0.0045   1.0000   0.2641
  -4.750  -0.4169   0.09438   0.08904  -0.0071   1.0000   0.2742
  -4.500  -0.4080   0.09106   0.08574  -0.0029   1.0000   0.2813
  -4.250  -0.4112   0.08869   0.08344  -0.0044   1.0000   0.2917
  -4.000  -0.4095   0.08633   0.08113  -0.0072   1.0000   0.3056
  -3.750  -0.4034   0.08327   0.07811  -0.0030   1.0000   0.3119
  -3.500  -0.1959   0.04570   0.03810  -0.0901   1.0000   0.1188
  -3.250  -0.1502   0.04156   0.03351  -0.0965   1.0000   0.1229
  -3.000  -0.1025   0.03814   0.02949  -0.1022   1.0000   0.1276
  -2.750  -0.0601   0.03583   0.02670  -0.1062   1.0000   0.1418
  -2.500  -0.0213   0.03410   0.02464  -0.1090   1.0000   0.1677
  -2.250   0.0110   0.03319   0.02383  -0.1105   1.0000   0.2155
  -2.000   0.0416   0.03262   0.02344  -0.1115   1.0000   0.2805
  -1.750   0.0705   0.03239   0.02337  -0.1120   1.0000   0.3532
  -1.500   0.0936   0.03247   0.02368  -0.1114   1.0000   0.4187
  -1.250   0.1147   0.03269   0.02406  -0.1103   1.0000   0.4817
  -1.000   0.1344   0.03300   0.02445  -0.1090   1.0000   0.5422
  -0.750   0.1498   0.03333   0.02492  -0.1067   1.0000   0.5952
  -0.500   0.1659   0.03370   0.02535  -0.1047   1.0000   0.6521
  -0.250   0.1773   0.03400   0.02576  -0.1017   1.0000   0.7049
   0.000   0.1872   0.03424   0.02606  -0.0986   1.0000   0.7632
   0.250   0.1916   0.03425   0.02619  -0.0943   1.0000   0.8285
   0.500   0.1858   0.03359   0.02574  -0.0889   1.0000   0.9362
   0.750   0.2288   0.03453   0.02630  -0.0966   1.0000   1.0000
   1.000   0.2651   0.03591   0.02729  -0.1013   0.9998   1.0000
   1.250   0.3281   0.03797   0.02895  -0.1101   0.9808   1.0000
   1.500   0.3802   0.03956   0.03026  -0.1163   0.9652   1.0000
   1.750   0.4223   0.04079   0.03129  -0.1205   0.9492   1.0000
   2.000   0.4620   0.04193   0.03228  -0.1241   0.9336   1.0000
   2.250   0.5016   0.04303   0.03325  -0.1275   0.9183   1.0000
   2.500   0.5400   0.04408   0.03420  -0.1305   0.9033   1.0000
   2.750   0.5781   0.04506   0.03511  -0.1333   0.8881   1.0000
   3.000   0.6154   0.04599   0.03600  -0.1358   0.8731   1.0000
   3.250   0.6525   0.04686   0.03684  -0.1382   0.8579   1.0000
   3.500   0.6893   0.04765   0.03763  -0.1403   0.8426   1.0000
   3.750   0.7256   0.04837   0.03839  -0.1422   0.8273   1.0000
   4.000   0.7616   0.04902   0.03907  -0.1439   0.8119   1.0000
   4.250   0.7977   0.04958   0.03968  -0.1455   0.7965   1.0000
   4.500   0.8341   0.05002   0.04022  -0.1468   0.7811   1.0000
   4.750   0.8707   0.05035   0.04064  -0.1480   0.7656   1.0000
   5.000   0.9080   0.05052   0.04091  -0.1491   0.7502   1.0000
   5.250   0.9463   0.05048   0.04104  -0.1500   0.7347   1.0000
   5.750   0.9977   0.05163   0.04243  -0.1490   0.6986   1.0000
   6.000   1.0344   0.05130   0.04227  -0.1491   0.6819   1.0000
   6.250   1.0772   0.05027   0.04148  -0.1493   0.6658   1.0000
   6.500   1.1295   0.04813   0.03957  -0.1497   0.6506   1.0000
   6.750   1.1949   0.04492   0.03668  -0.1511   0.6344   1.0000
   7.000   1.3057   0.03895   0.03112  -0.1574   0.6139   1.0000
   7.250   1.3470   0.03787   0.03021  -0.1571   0.5866   1.0000
   7.500   1.3950   0.03651   0.02898  -0.1576   0.5555   1.0000
   7.750   1.4378   0.03565   0.02811  -0.1576   0.5216   1.0000
   8.000   1.4618   0.03589   0.02834  -0.1555   0.4881   1.0000
   8.250   1.4800   0.03648   0.02893  -0.1527   0.4543   1.0000
   8.500   1.4980   0.03716   0.02957  -0.1500   0.4195   1.0000
   8.750   1.5189   0.03788   0.03006  -0.1477   0.3834   1.0000
   9.000   1.5279   0.03918   0.03131  -0.1441   0.3506   1.0000
   9.250   1.5361   0.04061   0.03267  -0.1405   0.3186   1.0000
   9.500   1.5442   0.04224   0.03420  -0.1370   0.2880   1.0000
   9.750   1.5516   0.04405   0.03589  -0.1336   0.2589   1.0000
  10.000   1.5585   0.04602   0.03773  -0.1302   0.2311   1.0000
  10.250   1.5600   0.04812   0.03980  -0.1263   0.2069   1.0000
  10.500   1.5575   0.05030   0.04195  -0.1220   0.1854   1.0000
  10.750   1.5514   0.05245   0.04412  -0.1175   0.1668   1.0000
  11.000   1.5541   0.05493   0.04632  -0.1145   0.1462   1.0000
  11.250   1.5517   0.05790   0.04941  -0.1109   0.1312   1.0000
  11.500   1.5555   0.06125   0.05284  -0.1083   0.1178   1.0000
  11.750   1.5702   0.06516   0.05677  -0.1071   0.1060   1.0000
  12.000   1.5567   0.06899   0.06117  -0.1031   0.1025   1.0000
  12.250   1.5568   0.07259   0.06497  -0.1008   0.0966   1.0000
  12.500   1.5584   0.07706   0.06965  -0.0991   0.0924   1.0000
  12.750   1.5384   0.08161   0.07465  -0.0961   0.0914   1.0000
  13.000   1.5174   0.08665   0.08009  -0.0940   0.0909   1.0000
  13.250   1.4934   0.09216   0.08597  -0.0927   0.0906   1.0000
  13.500   1.4679   0.09820   0.09234  -0.0924   0.0908   1.0000
  13.750   1.4410   0.10480   0.09919  -0.0932   0.0912   1.0000
  14.000   1.4133   0.11210   0.10673  -0.0953   0.0919   1.0000
  14.250   1.3874   0.11993   0.11476  -0.0984   0.0926   1.0000
  14.500   1.3623   0.12842   0.12340  -0.1025   0.0933   1.0000
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