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E207 (12.04%) (e207-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: E207 (12.04%) (e207-il)
Reynolds number: 50,000
Max Cl/Cd: 32.88 at α=8.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e207-il-50000-n5.txt
Download as CSV file: xf-e207-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E207  (12.04%)                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4523   0.09475   0.08776  -0.0376   1.0000   0.0511
  -9.750  -0.4575   0.08944   0.08252  -0.0404   1.0000   0.0511
  -9.500  -0.4649   0.08357   0.07673  -0.0438   1.0000   0.0509
  -9.250  -0.4751   0.07780   0.07101  -0.0475   1.0000   0.0506
  -9.000  -0.4911   0.07262   0.06589  -0.0506   1.0000   0.0503
  -8.750  -0.5085   0.06851   0.06179  -0.0512   1.0000   0.0500
  -8.500  -0.5238   0.06433   0.05754  -0.0515   1.0000   0.0499
  -8.250  -0.5360   0.06040   0.05348  -0.0510   1.0000   0.0498
  -8.000  -0.5455   0.05656   0.04944  -0.0500   1.0000   0.0500
  -7.750  -0.5515   0.05287   0.04548  -0.0485   1.0000   0.0503
  -7.500  -0.5526   0.04944   0.04173  -0.0467   1.0000   0.0505
  -7.250  -0.5505   0.04622   0.03816  -0.0448   1.0000   0.0507
  -7.000  -0.5456   0.04321   0.03475  -0.0428   1.0000   0.0511
  -6.750  -0.5379   0.04049   0.03161  -0.0407   1.0000   0.0516
  -6.500  -0.5279   0.03806   0.02894  -0.0387   1.0000   0.0524
  -6.250  -0.5164   0.03609   0.02681  -0.0368   1.0000   0.0536
  -6.000  -0.5045   0.03448   0.02502  -0.0349   1.0000   0.0553
  -5.750  -0.4925   0.03317   0.02354  -0.0329   1.0000   0.0584
  -5.500  -0.4687   0.03158   0.02158  -0.0329   0.9956   0.0627
  -5.250  -0.4302   0.02968   0.01951  -0.0354   0.9849   0.0673
  -5.000  -0.3926   0.02814   0.01779  -0.0375   0.9732   0.0736
  -4.750  -0.3565   0.02673   0.01626  -0.0394   0.9608   0.0842
  -4.500  -0.3209   0.02545   0.01492  -0.0413   0.9479   0.1057
  -4.250  -0.2861   0.02409   0.01378  -0.0434   0.9352   0.1495
  -4.000  -0.2509   0.02268   0.01283  -0.0459   0.9231   0.2339
  -3.750  -0.2181   0.02154   0.01224  -0.0474   0.9113   0.3430
  -3.500  -0.1867   0.02093   0.01195  -0.0479   0.8992   0.4553
  -3.250  -0.1579   0.02059   0.01174  -0.0475   0.8860   0.5393
  -3.000  -0.1293   0.02033   0.01155  -0.0468   0.8731   0.6057
  -2.750  -0.1006   0.02012   0.01135  -0.0460   0.8608   0.6639
  -2.500  -0.0708   0.01996   0.01117  -0.0453   0.8491   0.7178
  -2.250  -0.0370   0.01982   0.01099  -0.0451   0.8389   0.7691
  -2.000  -0.0001   0.01976   0.01084  -0.0456   0.8278   0.8176
  -1.750   0.0447   0.01976   0.01066  -0.0479   0.8170   0.8630
  -1.500   0.0983   0.01975   0.01041  -0.0521   0.8073   0.9024
  -1.250   0.1542   0.01970   0.01007  -0.0572   0.7974   0.9359
  -1.000   0.2082   0.01964   0.00977  -0.0625   0.7861   0.9656
  -0.750   0.2627   0.01950   0.00939  -0.0682   0.7752   0.9922
  -0.500   0.2919   0.01948   0.00917  -0.0692   0.7642   1.0000
  -0.250   0.3103   0.01958   0.00910  -0.0680   0.7534   1.0000
   0.000   0.3280   0.01977   0.00915  -0.0667   0.7421   1.0000
   0.250   0.3476   0.01998   0.00922  -0.0656   0.7320   1.0000
   0.500   0.3708   0.02014   0.00923  -0.0648   0.7233   1.0000
   0.750   0.3905   0.02045   0.00946  -0.0638   0.7129   1.0000
   1.000   0.4123   0.02073   0.00963  -0.0629   0.7039   1.0000
   1.250   0.4354   0.02099   0.00979  -0.0621   0.6955   1.0000
   1.500   0.4561   0.02136   0.01011  -0.0611   0.6861   1.0000
   1.750   0.4809   0.02160   0.01027  -0.0605   0.6789   1.0000
   2.000   0.5009   0.02203   0.01069  -0.0594   0.6694   1.0000
   2.250   0.5240   0.02237   0.01099  -0.0587   0.6617   1.0000
   2.500   0.5461   0.02277   0.01139  -0.0578   0.6533   1.0000
   2.750   0.5681   0.02320   0.01182  -0.0569   0.6453   1.0000
   3.000   0.5917   0.02356   0.01217  -0.0562   0.6376   1.0000
   3.250   0.6125   0.02408   0.01273  -0.0552   0.6292   1.0000
   3.500   0.6373   0.02441   0.01309  -0.0546   0.6221   1.0000
   3.750   0.6569   0.02501   0.01376  -0.0536   0.6133   1.0000
   4.000   0.6829   0.02531   0.01407  -0.0530   0.6067   1.0000
   4.250   0.7012   0.02599   0.01486  -0.0519   0.5973   1.0000
   4.500   0.7266   0.02633   0.01527  -0.0513   0.5904   1.0000
   4.750   0.7459   0.02697   0.01602  -0.0501   0.5809   1.0000
   5.000   0.7673   0.02750   0.01664  -0.0492   0.5723   1.0000
   5.250   0.7917   0.02784   0.01708  -0.0484   0.5640   1.0000
   5.500   0.8099   0.02851   0.01792  -0.0471   0.5537   1.0000
   5.750   0.8332   0.02888   0.01839  -0.0462   0.5447   1.0000
   6.000   0.8565   0.02919   0.01883  -0.0452   0.5348   1.0000
   6.250   0.8745   0.02978   0.01958  -0.0438   0.5233   1.0000
   6.500   0.8948   0.03019   0.02014  -0.0425   0.5118   1.0000
   6.750   0.9171   0.03042   0.02054  -0.0412   0.5002   1.0000
   7.000   0.9401   0.03052   0.02079  -0.0400   0.4878   1.0000
   7.250   0.9616   0.03065   0.02105  -0.0385   0.4744   1.0000
   7.500   0.9802   0.03087   0.02145  -0.0368   0.4594   1.0000
   7.750   0.9968   0.03116   0.02192  -0.0348   0.4432   1.0000
   8.000   1.0125   0.03141   0.02239  -0.0328   0.4256   1.0000
   8.250   1.0295   0.03147   0.02260  -0.0307   0.4067   1.0000
   8.500   1.0430   0.03174   0.02300  -0.0283   0.3860   1.0000
   8.750   1.0544   0.03207   0.02344  -0.0257   0.3629   1.0000
   9.000   1.0620   0.03268   0.02414  -0.0229   0.3375   1.0000
   9.250   1.0680   0.03340   0.02487  -0.0201   0.3104   1.0000
   9.500   1.0696   0.03434   0.02576  -0.0168   0.2835   1.0000
   9.750   1.0691   0.03564   0.02700  -0.0138   0.2571   1.0000
  10.000   1.0668   0.03730   0.02851  -0.0112   0.2326   1.0000
  10.250   1.0634   0.03936   0.03049  -0.0091   0.2104   1.0000
  10.500   1.0594   0.04167   0.03266  -0.0074   0.1913   1.0000
  10.750   1.0558   0.04422   0.03518  -0.0062   0.1732   1.0000
  11.000   1.0529   0.04688   0.03780  -0.0052   0.1575   1.0000
  11.250   1.0503   0.04966   0.04055  -0.0044   0.1434   1.0000
  11.500   1.0485   0.05247   0.04334  -0.0039   0.1308   1.0000
  11.750   1.0473   0.05534   0.04621  -0.0034   0.1194   1.0000
  12.000   1.0461   0.05824   0.04907  -0.0030   0.1093   1.0000
  12.250   1.0455   0.06124   0.05213  -0.0029   0.0996   1.0000
  12.500   1.0450   0.06438   0.05538  -0.0028   0.0906   1.0000
  12.750   1.0435   0.06758   0.05857  -0.0029   0.0828   1.0000
  13.000   1.0423   0.07095   0.06212  -0.0031   0.0755   1.0000
  13.250   1.0401   0.07450   0.06576  -0.0035   0.0692   1.0000
  13.500   1.0375   0.07820   0.06958  -0.0041   0.0636   1.0000
  13.750   1.0364   0.08176   0.07317  -0.0046   0.0590   1.0000
  14.000   1.0313   0.08628   0.07799  -0.0058   0.0550   1.0000
  14.250   1.0280   0.09031   0.08210  -0.0070   0.0515   1.0000
  14.500   1.0263   0.09422   0.08602  -0.0079   0.0486   1.0000
  14.750   1.0158   0.10019   0.09233  -0.0103   0.0470   1.0000
  15.000   1.0042   0.10659   0.09900  -0.0131   0.0458   1.0000
  15.250   0.9896   0.11379   0.10644  -0.0167   0.0448   1.0000
  15.500   0.9718   0.12219   0.11506  -0.0212   0.0446   1.0000
  15.750   0.9483   0.13274   0.12580  -0.0271   0.0454   1.0000
  16.000   0.9222   0.14504   0.13818  -0.0341   0.0464   1.0000
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