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E216 (10.4%) (e216-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: E216 (10.4%) (e216-il)
Reynolds number: 50,000
Max Cl/Cd: 42.99 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e216-il-50000-n5.txt
Download as CSV file: xf-e216-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3374   0.12223   0.11543  -0.0317   1.0000   0.1008
  -8.500  -0.3393   0.11988   0.11314  -0.0311   1.0000   0.1019
  -8.000  -0.3725   0.11085   0.10429  -0.0348   1.0000   0.0553
  -7.750  -0.3693   0.10821   0.10169  -0.0329   1.0000   0.0547
  -7.500  -0.3736   0.10572   0.09926  -0.0316   1.0000   0.0543
  -7.250  -0.3777   0.10340   0.09702  -0.0301   1.0000   0.0536
  -7.000  -0.3847   0.10113   0.09484  -0.0285   1.0000   0.0528
  -6.750  -0.3937   0.09893   0.09273  -0.0269   1.0000   0.0521
  -6.500  -0.4015   0.09639   0.09028  -0.0260   1.0000   0.0512
  -6.250  -0.4075   0.09344   0.08741  -0.0261   1.0000   0.0502
  -6.000  -0.4123   0.08996   0.08402  -0.0273   1.0000   0.0492
  -5.750  -0.4148   0.08564   0.07976  -0.0300   1.0000   0.0481
  -5.500  -0.3992   0.07264   0.06664  -0.0486   0.9981   0.0445
  -5.250  -0.3684   0.06537   0.05917  -0.0593   0.9933   0.0441
  -5.000  -0.3277   0.05697   0.05036  -0.0728   0.9891   0.0436
  -4.750  -0.2737   0.04849   0.04111  -0.0876   0.9869   0.0436
  -4.500  -0.2151   0.04187   0.03341  -0.0994   0.9856   0.0447
  -4.250  -0.1769   0.03958   0.03094  -0.1038   0.9817   0.0483
  -4.000  -0.1310   0.03682   0.02754  -0.1091   0.9788   0.0526
  -3.750  -0.0867   0.03451   0.02465  -0.1131   0.9763   0.0563
  -3.500  -0.0499   0.03322   0.02319  -0.1157   0.9718   0.0638
  -3.250  -0.0111   0.03204   0.02182  -0.1184   0.9677   0.0765
  -3.000   0.0294   0.03101   0.02073  -0.1217   0.9638   0.1035
  -2.750   0.0694   0.03014   0.01992  -0.1250   0.9588   0.1544
  -2.500   0.1125   0.02960   0.01951  -0.1288   0.9548   0.2197
  -2.250   0.1484   0.02934   0.01933  -0.1311   0.9484   0.2822
  -2.000   0.1871   0.02925   0.01929  -0.1336   0.9431   0.3451
  -1.750   0.2199   0.02923   0.01930  -0.1349   0.9361   0.3989
  -1.500   0.2559   0.02926   0.01935  -0.1365   0.9301   0.4537
  -1.250   0.2864   0.02930   0.01941  -0.1371   0.9224   0.5020
  -1.000   0.3206   0.02933   0.01944  -0.1383   0.9159   0.5510
  -0.750   0.3478   0.02937   0.01953  -0.1381   0.9073   0.5945
  -0.500   0.3809   0.02936   0.01953  -0.1388   0.9008   0.6415
  -0.250   0.4045   0.02939   0.01958  -0.1378   0.8911   0.6844
   0.000   0.4362   0.02924   0.01947  -0.1380   0.8851   0.7331
   0.500   0.4729   0.02900   0.01933  -0.1337   0.8647   0.8373
   0.750   0.4964   0.02835   0.01872  -0.1323   0.8559   1.0000
   1.250   0.5691   0.02883   0.01883  -0.1367   0.8372   1.0000
   1.500   0.6053   0.02898   0.01884  -0.1385   0.8281   1.0000
   1.750   0.6370   0.02922   0.01898  -0.1396   0.8176   1.0000
   2.000   0.6784   0.02911   0.01878  -0.1418   0.8110   1.0000
   2.250   0.7068   0.02937   0.01899  -0.1421   0.7992   1.0000
   2.500   0.7393   0.02946   0.01905  -0.1430   0.7891   1.0000
   2.750   0.7779   0.02925   0.01883  -0.1444   0.7813   1.0000
   3.000   0.8064   0.02943   0.01901  -0.1446   0.7692   1.0000
   3.250   0.8391   0.02941   0.01901  -0.1452   0.7587   1.0000
   3.500   0.8785   0.02906   0.01872  -0.1465   0.7502   1.0000
   3.750   0.9072   0.02917   0.01887  -0.1465   0.7372   1.0000
   4.000   0.9379   0.02918   0.01893  -0.1466   0.7246   1.0000
   4.250   0.9714   0.02905   0.01890  -0.1471   0.7125   1.0000
   4.500   1.0093   0.02870   0.01863  -0.1480   0.7011   1.0000
   4.750   1.0448   0.02848   0.01849  -0.1487   0.6878   1.0000
   5.000   1.0764   0.02844   0.01856  -0.1488   0.6726   1.0000
   5.250   1.1088   0.02837   0.01859  -0.1490   0.6568   1.0000
   5.500   1.1371   0.02849   0.01880  -0.1486   0.6390   1.0000
   5.750   1.1638   0.02869   0.01913  -0.1479   0.6201   1.0000
   6.000   1.1921   0.02883   0.01935  -0.1475   0.6005   1.0000
   6.250   1.2230   0.02890   0.01949  -0.1473   0.5803   1.0000
   6.500   1.2464   0.02927   0.01997  -0.1462   0.5586   1.0000
   6.750   1.2704   0.02964   0.02042  -0.1451   0.5361   1.0000
   7.000   1.2930   0.03008   0.02091  -0.1438   0.5131   1.0000
   7.250   1.3125   0.03064   0.02154  -0.1421   0.4892   1.0000
   7.500   1.3306   0.03129   0.02226  -0.1402   0.4649   1.0000
   7.750   1.3479   0.03198   0.02298  -0.1382   0.4405   1.0000
   8.000   1.3612   0.03287   0.02393  -0.1358   0.4157   1.0000
   8.250   1.3752   0.03377   0.02482  -0.1335   0.3913   1.0000
   8.500   1.3856   0.03485   0.02601  -0.1308   0.3668   1.0000
   8.750   1.3955   0.03601   0.02718  -0.1282   0.3428   1.0000
   9.000   1.4036   0.03731   0.02852  -0.1255   0.3191   1.0000
   9.250   1.4105   0.03875   0.02999  -0.1227   0.2961   1.0000
   9.500   1.4160   0.04032   0.03159  -0.1200   0.2738   1.0000
   9.750   1.4206   0.04205   0.03334  -0.1173   0.2526   1.0000
  10.000   1.4241   0.04395   0.03532  -0.1148   0.2318   1.0000
  10.250   1.4266   0.04600   0.03740  -0.1123   0.2130   1.0000
  10.500   1.4280   0.04825   0.03965  -0.1100   0.1951   1.0000
  10.750   1.4293   0.05065   0.04215  -0.1079   0.1779   1.0000
  11.000   1.4292   0.05327   0.04483  -0.1059   0.1619   1.0000
  11.250   1.4283   0.05608   0.04771  -0.1041   0.1472   1.0000
  11.500   1.4257   0.05915   0.05085  -0.1025   0.1334   1.0000
  11.750   1.4214   0.06249   0.05425  -0.1012   0.1205   1.0000
  12.000   1.4153   0.06613   0.05797  -0.1002   0.1085   1.0000
  12.250   1.4084   0.07003   0.06188  -0.0996   0.0982   1.0000
  12.500   1.4018   0.07413   0.06611  -0.0993   0.0881   1.0000
  12.750   1.3964   0.07834   0.07047  -0.0992   0.0792   1.0000
  13.000   1.3903   0.08271   0.07489  -0.0994   0.0728   1.0000
  13.250   1.3859   0.08712   0.07949  -0.0996   0.0663   1.0000
  13.500   1.3812   0.09155   0.08397  -0.1001   0.0618   1.0000
  13.750   1.3785   0.09604   0.08874  -0.1006   0.0570   1.0000
  14.000   1.3756   0.10037   0.09314  -0.1013   0.0538   1.0000
  14.250   1.3738   0.10481   0.09775  -0.1021   0.0509   1.0000
  14.500   1.3696   0.10990   0.10316  -0.1035   0.0483   1.0000
  14.750   1.3647   0.11505   0.10852  -0.1053   0.0461   1.0000
  15.000   1.3617   0.11977   0.11334  -0.1071   0.0443   1.0000
  15.250   1.3602   0.12427   0.11792  -0.1087   0.0428   1.0000
  15.500   1.3502   0.13116   0.12516  -0.1122   0.0420   1.0000
  15.750   1.3378   0.13885   0.13313  -0.1166   0.0415   1.0000
  16.000   1.3229   0.14754   0.14209  -0.1220   0.0413   1.0000
  16.250   1.3052   0.15755   0.15234  -0.1287   0.0413   1.0000
  16.500   1.2849   0.16925   0.16422  -0.1367   0.0416   1.0000
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