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E216 (10.4%) (e216-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: E216 (10.4%) (e216-il)
Reynolds number: 100,000
Max Cl/Cd: 68.53 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e216-il-100000-n5.txt
Download as CSV file: xf-e216-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3594   0.12077   0.11599  -0.0324   1.0000   0.0547
  -8.750  -0.3665   0.11847   0.11377  -0.0325   1.0000   0.0550
  -8.500  -0.3710   0.11599   0.11134  -0.0320   1.0000   0.0550
  -8.250  -0.3761   0.11328   0.10870  -0.0327   0.9994   0.0552
  -8.000  -0.3589   0.10567   0.10102  -0.0322   0.9980   0.0343
  -7.500  -0.3476   0.09473   0.09011  -0.0414   0.9892   0.0284
  -7.250  -0.3368   0.09125   0.08663  -0.0444   0.9852   0.0278
  -7.000  -0.3320   0.08762   0.08303  -0.0469   0.9792   0.0273
  -6.750  -0.3255   0.08337   0.07879  -0.0508   0.9731   0.0268
  -6.250  -0.2983   0.05325   0.04833  -0.0912   0.9555   0.0232
  -6.000  -0.2610   0.04398   0.03841  -0.1064   0.9510   0.0230
  -5.750  -0.2163   0.03722   0.03078  -0.1173   0.9483   0.0231
  -5.500  -0.1740   0.03335   0.02631  -0.1236   0.9462   0.0236
  -5.250  -0.1355   0.03150   0.02422  -0.1276   0.9439   0.0253
  -5.000  -0.0933   0.02935   0.02158  -0.1318   0.9423   0.0274
  -4.750  -0.0565   0.02752   0.01931  -0.1343   0.9393   0.0285
  -4.500  -0.0227   0.02609   0.01773  -0.1362   0.9353   0.0298
  -4.250   0.0146   0.02497   0.01649  -0.1386   0.9322   0.0321
  -4.000   0.0545   0.02398   0.01530  -0.1413   0.9298   0.0361
  -3.750   0.0935   0.02317   0.01439  -0.1441   0.9271   0.0440
  -3.500   0.1275   0.02228   0.01351  -0.1459   0.9218   0.0581
  -3.250   0.1667   0.02148   0.01289  -0.1488   0.9184   0.1035
  -3.000   0.2064   0.02092   0.01252  -0.1517   0.9156   0.1699
  -2.750   0.2391   0.02059   0.01226  -0.1530   0.9104   0.2158
  -2.500   0.2722   0.02032   0.01205  -0.1543   0.9049   0.2618
  -2.250   0.3101   0.02003   0.01180  -0.1564   0.9015   0.3110
  -2.000   0.3414   0.01986   0.01169  -0.1572   0.8955   0.3529
  -1.750   0.3744   0.01968   0.01153  -0.1582   0.8897   0.3941
  -1.250   0.4402   0.01934   0.01128  -0.1600   0.8786   0.4727
  -1.000   0.4750   0.01911   0.01108  -0.1612   0.8736   0.5102
  -0.750   0.5130   0.01878   0.01079  -0.1628   0.8705   0.5482
  -0.500   0.5378   0.01877   0.01083  -0.1620   0.8610   0.5800
  -0.250   0.5740   0.01844   0.01053  -0.1632   0.8569   0.6161
   0.000   0.6007   0.01837   0.01051  -0.1627   0.8482   0.6483
   0.250   0.6347   0.01806   0.01024  -0.1634   0.8428   0.6829
   0.500   0.6619   0.01792   0.01017  -0.1628   0.8343   0.7157
   0.750   0.6936   0.01761   0.00991  -0.1630   0.8278   0.7504
   1.000   0.7187   0.01745   0.00982  -0.1619   0.8184   0.7853
   1.250   0.7494   0.01706   0.00948  -0.1618   0.8116   0.8244
   1.500   0.7689   0.01688   0.00936  -0.1596   0.8005   0.8700
   1.750   0.7924   0.01640   0.00893  -0.1580   0.7907   1.0000
   2.000   0.8317   0.01626   0.00873  -0.1601   0.7814   1.0000
   2.250   0.8653   0.01626   0.00869  -0.1612   0.7694   1.0000
   2.500   0.9017   0.01622   0.00860  -0.1627   0.7576   1.0000
   2.750   0.9394   0.01616   0.00853  -0.1645   0.7452   1.0000
   3.000   0.9755   0.01615   0.00847  -0.1659   0.7314   1.0000
   3.250   1.0094   0.01619   0.00848  -0.1669   0.7164   1.0000
   3.500   1.0414   0.01629   0.00857  -0.1676   0.7000   1.0000
   3.750   1.0722   0.01642   0.00868  -0.1680   0.6827   1.0000
   4.000   1.1020   0.01660   0.00883  -0.1682   0.6644   1.0000
   4.250   1.1313   0.01680   0.00902  -0.1683   0.6453   1.0000
   4.750   1.1854   0.01734   0.00949  -0.1677   0.6040   1.0000
   5.000   1.2110   0.01767   0.00980  -0.1671   0.5824   1.0000
   5.250   1.2354   0.01805   0.01014  -0.1663   0.5606   1.0000
   5.500   1.2584   0.01846   0.01052  -0.1653   0.5377   1.0000
   5.750   1.2807   0.01891   0.01093  -0.1642   0.5146   1.0000
   6.000   1.3014   0.01940   0.01141  -0.1628   0.4903   1.0000
   6.250   1.3214   0.01994   0.01191  -0.1613   0.4661   1.0000
   6.500   1.3402   0.02052   0.01244  -0.1596   0.4415   1.0000
   6.750   1.3580   0.02113   0.01303  -0.1578   0.4168   1.0000
   7.250   1.3894   0.02249   0.01435  -0.1535   0.3678   1.0000
   7.500   1.4034   0.02326   0.01508  -0.1511   0.3433   1.0000
   7.750   1.4166   0.02409   0.01587  -0.1487   0.3186   1.0000
   8.000   1.4291   0.02498   0.01675  -0.1462   0.2939   1.0000
   8.500   1.4518   0.02698   0.01869  -0.1411   0.2468   1.0000
   8.750   1.4615   0.02812   0.01979  -0.1385   0.2249   1.0000
   9.000   1.4718   0.02927   0.02096  -0.1360   0.2035   1.0000
   9.250   1.4796   0.03061   0.02227  -0.1333   0.1826   1.0000
   9.500   1.4875   0.03201   0.02365  -0.1308   0.1606   1.0000
   9.750   1.4926   0.03363   0.02518  -0.1281   0.1386   1.0000
  10.000   1.4982   0.03531   0.02679  -0.1256   0.1159   1.0000
  10.250   1.5027   0.03714   0.02855  -0.1232   0.0971   1.0000
  10.500   1.5080   0.03896   0.03039  -0.1209   0.0826   1.0000
  10.750   1.5121   0.04093   0.03240  -0.1186   0.0699   1.0000
  11.000   1.5148   0.04311   0.03463  -0.1164   0.0588   1.0000
  11.250   1.5157   0.04553   0.03710  -0.1142   0.0498   1.0000
  11.500   1.5140   0.04828   0.03990  -0.1120   0.0431   1.0000
  11.750   1.5132   0.05105   0.04283  -0.1101   0.0378   1.0000
  12.000   1.5083   0.05435   0.04620  -0.1083   0.0347   1.0000
  12.250   1.5059   0.05751   0.04956  -0.1068   0.0320   1.0000
  12.500   1.5023   0.06090   0.05312  -0.1056   0.0297   1.0000
  12.750   1.4970   0.06464   0.05698  -0.1048   0.0282   1.0000
  13.000   1.4914   0.06857   0.06106  -0.1042   0.0268   1.0000
  13.250   1.4882   0.07238   0.06509  -0.1038   0.0255   1.0000
  13.500   1.4842   0.07641   0.06933  -0.1037   0.0243   1.0000
  13.750   1.4794   0.08068   0.07376  -0.1040   0.0234   1.0000
  14.000   1.4742   0.08512   0.07836  -0.1045   0.0228   1.0000
  14.250   1.4688   0.08971   0.08309  -0.1052   0.0222   1.0000
  14.500   1.4631   0.09442   0.08792  -0.1061   0.0218   1.0000
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