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E222 (10.17%) (e222-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: E222 (10.17%) (e222-il)
Reynolds number: 200,000
Max Cl/Cd: 71.32 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e222-il-200000-n5.txt
Download as CSV file: xf-e222-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E222  (10.17%)                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4647   0.08707   0.08345  -0.0385   1.0000   0.0187
  -9.500  -0.4733   0.08188   0.07832  -0.0405   1.0000   0.0184
  -9.250  -0.4866   0.07590   0.07240  -0.0428   1.0000   0.0180
  -9.000  -0.5089   0.06809   0.06468  -0.0464   1.0000   0.0175
  -8.750  -0.5606   0.05584   0.05241  -0.0543   1.0000   0.0169
  -8.500  -0.5931   0.04908   0.04540  -0.0558   1.0000   0.0166
  -8.250  -0.6137   0.04310   0.03900  -0.0555   1.0000   0.0163
  -8.000  -0.6199   0.03830   0.03373  -0.0546   1.0000   0.0160
  -7.750  -0.6000   0.03368   0.02855  -0.0573   0.9967   0.0160
  -7.500  -0.5733   0.03020   0.02457  -0.0598   0.9933   0.0160
  -7.250  -0.5458   0.02753   0.02148  -0.0615   0.9895   0.0162
  -7.000  -0.5159   0.02531   0.01890  -0.0632   0.9862   0.0164
  -6.750  -0.4840   0.02348   0.01678  -0.0649   0.9836   0.0169
  -6.500  -0.4557   0.02197   0.01501  -0.0657   0.9793   0.0172
  -6.250  -0.4251   0.02063   0.01348  -0.0667   0.9754   0.0177
  -6.000  -0.3925   0.01948   0.01216  -0.0681   0.9724   0.0183
  -5.750  -0.3614   0.01860   0.01115  -0.0691   0.9685   0.0196
  -5.500  -0.3318   0.01776   0.01019  -0.0698   0.9635   0.0203
  -5.250  -0.2988   0.01687   0.00918  -0.0711   0.9600   0.0207
  -5.000  -0.2654   0.01589   0.00812  -0.0726   0.9568   0.0215
  -4.750  -0.2370   0.01520   0.00735  -0.0730   0.9505   0.0226
  -4.500  -0.2029   0.01461   0.00667  -0.0744   0.9466   0.0242
  -4.250  -0.1666   0.01410   0.00604  -0.0763   0.9439   0.0267
  -4.000  -0.1386   0.01362   0.00553  -0.0763   0.9366   0.0315
  -3.750  -0.1043   0.01290   0.00500  -0.0780   0.9326   0.0675
  -3.500  -0.0699   0.01223   0.00461  -0.0797   0.9287   0.1341
  -3.250  -0.0404   0.01173   0.00433  -0.0803   0.9214   0.1961
  -3.000  -0.0054   0.01128   0.00407  -0.0820   0.9169   0.2562
  -2.750   0.0241   0.01082   0.00391  -0.0826   0.9090   0.3356
  -2.500   0.0576   0.01039   0.00375  -0.0839   0.9031   0.4176
  -2.250   0.0879   0.01014   0.00362  -0.0843   0.8947   0.4650
  -2.000   0.1220   0.00990   0.00346  -0.0855   0.8879   0.5075
  -1.750   0.1515   0.00972   0.00336  -0.0856   0.8780   0.5473
  -1.500   0.1826   0.00954   0.00326  -0.0861   0.8688   0.5860
  -1.250   0.2139   0.00939   0.00316  -0.0866   0.8592   0.6230
  -1.000   0.2423   0.00928   0.00311  -0.0864   0.8475   0.6566
  -0.750   0.2707   0.00918   0.00306  -0.0862   0.8356   0.6894
  -0.500   0.2986   0.00911   0.00303  -0.0858   0.8233   0.7207
  -0.250   0.3258   0.00906   0.00300  -0.0854   0.8103   0.7500
   0.000   0.3523   0.00903   0.00299  -0.0847   0.7967   0.7776
   0.250   0.3780   0.00901   0.00298  -0.0838   0.7824   0.8044
   0.500   0.4030   0.00901   0.00298  -0.0828   0.7674   0.8311
   0.750   0.4273   0.00902   0.00298  -0.0816   0.7521   0.8578
   1.000   0.4514   0.00903   0.00298  -0.0804   0.7363   0.8839
   1.250   0.4765   0.00905   0.00296  -0.0795   0.7200   0.9106
   1.500   0.5048   0.00908   0.00296  -0.0792   0.7031   0.9384
   1.750   0.5389   0.00913   0.00294  -0.0804   0.6849   0.9681
   2.000   0.5718   0.00921   0.00295  -0.0815   0.6652   1.0000
   2.250   0.5977   0.00936   0.00303  -0.0811   0.6459   1.0000
   2.500   0.6235   0.00954   0.00311  -0.0807   0.6264   1.0000
   2.750   0.6491   0.00971   0.00321  -0.0802   0.6059   1.0000
   3.000   0.6745   0.00992   0.00333  -0.0797   0.5849   1.0000
   3.250   0.6998   0.01013   0.00348  -0.0792   0.5628   1.0000
   3.500   0.7246   0.01037   0.00364  -0.0786   0.5397   1.0000
   3.750   0.7493   0.01062   0.00381  -0.0780   0.5157   1.0000
   4.000   0.7738   0.01089   0.00401  -0.0773   0.4908   1.0000
   4.250   0.7979   0.01119   0.00424  -0.0766   0.4651   1.0000
   4.500   0.8216   0.01152   0.00448  -0.0759   0.4385   1.0000
   4.750   0.8451   0.01187   0.00475  -0.0751   0.4106   1.0000
   5.000   0.8683   0.01225   0.00504  -0.0743   0.3823   1.0000
   5.250   0.8912   0.01265   0.00536  -0.0735   0.3537   1.0000
   5.500   0.9139   0.01309   0.00573  -0.0727   0.3240   1.0000
   5.750   0.9361   0.01357   0.00611  -0.0718   0.2931   1.0000
   6.000   0.9579   0.01409   0.00653  -0.0709   0.2613   1.0000
   6.250   0.9794   0.01464   0.00699  -0.0700   0.2310   1.0000
   6.500   0.9998   0.01530   0.00751  -0.0689   0.1968   1.0000
   6.750   1.0192   0.01607   0.00808  -0.0678   0.1575   1.0000
   7.000   1.0386   0.01684   0.00868  -0.0667   0.1246   1.0000
   7.250   1.0587   0.01756   0.00931  -0.0656   0.1020   1.0000
   7.500   1.0779   0.01834   0.00998  -0.0645   0.0785   1.0000
   7.750   1.0967   0.01914   0.01070  -0.0633   0.0581   1.0000
   8.000   1.1143   0.02006   0.01154  -0.0619   0.0393   1.0000
   8.250   1.1300   0.02113   0.01251  -0.0603   0.0237   1.0000
   8.500   1.1461   0.02214   0.01354  -0.0586   0.0171   1.0000
   8.750   1.1626   0.02306   0.01456  -0.0570   0.0147   1.0000
   9.000   1.1773   0.02409   0.01567  -0.0552   0.0133   1.0000
   9.250   1.1897   0.02515   0.01685  -0.0530   0.0125   1.0000
   9.500   1.2014   0.02618   0.01802  -0.0507   0.0120   1.0000
   9.750   1.2113   0.02732   0.01933  -0.0483   0.0115   1.0000
  10.000   1.2201   0.02854   0.02069  -0.0459   0.0110   1.0000
  10.250   1.2281   0.02983   0.02210  -0.0436   0.0105   1.0000
  10.500   1.2352   0.03120   0.02359  -0.0414   0.0101   1.0000
  10.750   1.2406   0.03274   0.02524  -0.0392   0.0096   1.0000
  11.000   1.2411   0.03475   0.02735  -0.0368   0.0092   1.0000
  11.250   1.2436   0.03671   0.02944  -0.0349   0.0089   1.0000
  11.500   1.2471   0.03868   0.03157  -0.0332   0.0088   1.0000
  11.750   1.2496   0.04085   0.03391  -0.0317   0.0086   1.0000
  12.000   1.2515   0.04319   0.03642  -0.0305   0.0085   1.0000
  12.250   1.2523   0.04577   0.03916  -0.0295   0.0084   1.0000
  12.500   1.2522   0.04854   0.04214  -0.0287   0.0083   1.0000
  12.750   1.2508   0.05160   0.04539  -0.0282   0.0081   1.0000
  13.000   1.2486   0.05489   0.04887  -0.0280   0.0081   1.0000
  13.250   1.2447   0.05853   0.05270  -0.0281   0.0080   1.0000
  13.500   1.2393   0.06250   0.05688  -0.0287   0.0079   1.0000
  13.750   1.2325   0.06686   0.06145  -0.0297   0.0079   1.0000
  14.000   1.2240   0.07165   0.06644  -0.0311   0.0079   1.0000
  14.250   1.2140   0.07692   0.07193  -0.0331   0.0078   1.0000
  14.500   1.2025   0.08275   0.07796  -0.0357   0.0078   1.0000
  14.750   1.1898   0.08910   0.08453  -0.0389   0.0078   1.0000
  15.000   1.1755   0.09613   0.09176  -0.0427   0.0078   1.0000
  15.250   1.1606   0.10366   0.09949  -0.0470   0.0078   1.0000
  15.500   1.1445   0.11186   0.10787  -0.0520   0.0079   1.0000
  15.750   1.1272   0.12081   0.11702  -0.0575   0.0079   1.0000
  16.000   1.1090   0.13051   0.12689  -0.0636   0.0080   1.0000
  16.250   1.0893   0.14112   0.13767  -0.0704   0.0081   1.0000
  16.500   1.0669   0.15329   0.14999  -0.0780   0.0082   1.0000
  16.750   1.0390   0.16832   0.16512  -0.0870   0.0085   1.0000
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