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E220 (11.48%) (e220-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: E220 (11.48%) (e220-il)
Reynolds number: 200,000
Max Cl/Cd: 76.03 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e220-il-200000.txt
Download as CSV file: xf-e220-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E220  (11.48%)                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.3563   0.10925   0.10641  -0.0161   1.0000   0.0464
 -10.500  -0.3508   0.10541   0.10259  -0.0180   1.0000   0.0479
 -10.250  -0.4606   0.10604   0.10290  -0.0170   1.0000   0.0445
 -10.000  -0.4503   0.10311   0.09998  -0.0170   1.0000   0.0458
  -9.750  -0.4446   0.09963   0.09655  -0.0185   1.0000   0.0471
  -9.500  -0.4412   0.09578   0.09274  -0.0207   1.0000   0.0487
  -9.250  -0.4398   0.09157   0.08859  -0.0237   1.0000   0.0504
  -9.000  -0.4422   0.08655   0.08364  -0.0287   1.0000   0.0524
  -8.750  -0.3882   0.06879   0.06596  -0.0406   0.8921   0.0562
  -8.500  -0.3799   0.06662   0.06374  -0.0382   0.8815   0.0574
  -8.250  -0.3898   0.06214   0.05923  -0.0404   0.8722   0.0580
  -8.000  -0.4066   0.05715   0.05419  -0.0435   0.8629   0.0585
  -7.750  -0.4209   0.05336   0.05031  -0.0433   0.8549   0.0591
  -7.500  -0.4278   0.04926   0.04611  -0.0435   0.8475   0.0603
  -7.250  -0.4335   0.04507   0.04176  -0.0433   0.8414   0.0622
  -7.000  -0.4647   0.05177   0.04794  -0.0456   0.8491   0.0633
  -6.750  -0.4723   0.04761   0.04313  -0.0436   0.8421   0.0691
  -6.500  -0.4557   0.04454   0.04010  -0.0433   0.8353   0.0709
  -6.250  -0.4545   0.03352   0.02739  -0.0369   0.8302   0.0327
  -6.000  -0.4394   0.02908   0.02268  -0.0355   0.8247   0.0306
  -5.750  -0.4204   0.02624   0.01938  -0.0338   0.8191   0.0299
  -5.500  -0.3990   0.02407   0.01679  -0.0323   0.8147   0.0300
  -5.250  -0.3742   0.02295   0.01535  -0.0315   0.8094   0.0318
  -5.000  -0.3496   0.02115   0.01325  -0.0306   0.8043   0.0332
  -4.750  -0.3253   0.01939   0.01138  -0.0298   0.8004   0.0349
  -4.500  -0.2999   0.01834   0.01030  -0.0292   0.7957   0.0375
  -4.250  -0.2747   0.01756   0.00942  -0.0285   0.7909   0.0419
  -4.000  -0.2525   0.01660   0.00846  -0.0274   0.7868   0.0499
  -3.750  -0.2297   0.01579   0.00763  -0.0263   0.7827   0.0630
  -3.500  -0.2078   0.01486   0.00692  -0.0253   0.7780   0.1060
  -3.250  -0.1881   0.01387   0.00649  -0.0241   0.7739   0.2179
  -3.000  -0.1688   0.01316   0.00625  -0.0226   0.7706   0.3423
  -2.750  -0.1508   0.01247   0.00616  -0.0211   0.7657   0.4827
  -2.500  -0.1359   0.01168   0.00613  -0.0182   0.7616   0.6622
  -2.250  -0.0569   0.01140   0.00639  -0.0270   0.7590   0.8758
  -2.000  -0.0050   0.01183   0.00662  -0.0308   0.7562   0.9190
  -1.750   0.0416   0.01229   0.00695  -0.0340   0.7521   0.9459
  -1.500   0.0938   0.01258   0.00707  -0.0387   0.7481   0.9638
  -1.250   0.1466   0.01271   0.00703  -0.0436   0.7446   0.9786
  -1.000   0.2012   0.01266   0.00681  -0.0492   0.7417   0.9913
  -0.750   0.2507   0.01251   0.00658  -0.0542   0.7371   1.0000
  -0.500   0.2734   0.01251   0.00651  -0.0536   0.7324   1.0000
  -0.250   0.2959   0.01252   0.00643  -0.0528   0.7287   1.0000
   0.000   0.3192   0.01258   0.00644  -0.0523   0.7245   1.0000
   0.250   0.3431   0.01264   0.00647  -0.0519   0.7192   1.0000
   0.500   0.3664   0.01266   0.00642  -0.0512   0.7150   1.0000
   0.750   0.3901   0.01272   0.00644  -0.0505   0.7108   1.0000
   1.000   0.4144   0.01281   0.00652  -0.0502   0.7048   1.0000
   1.250   0.4382   0.01283   0.00649  -0.0494   0.7003   1.0000
   1.500   0.4623   0.01291   0.00654  -0.0488   0.6958   1.0000
   1.750   0.4867   0.01300   0.00666  -0.0484   0.6896   1.0000
   2.000   0.5107   0.01300   0.00661  -0.0476   0.6850   1.0000
   2.250   0.5349   0.01310   0.00673  -0.0470   0.6791   1.0000
   2.500   0.5592   0.01313   0.00676  -0.0464   0.6729   1.0000
   2.750   0.5835   0.01311   0.00670  -0.0454   0.6686   1.0000
   3.000   0.6077   0.01323   0.00690  -0.0450   0.6608   1.0000
   3.250   0.6322   0.01318   0.00681  -0.0441   0.6555   1.0000
   3.500   0.6563   0.01326   0.00696  -0.0435   0.6478   1.0000
   3.750   0.6810   0.01318   0.00688  -0.0427   0.6414   1.0000
   4.000   0.7051   0.01323   0.00699  -0.0420   0.6333   1.0000
   4.250   0.7299   0.01312   0.00686  -0.0411   0.6265   1.0000
   4.500   0.7539   0.01313   0.00697  -0.0404   0.6171   1.0000
   4.750   0.7788   0.01301   0.00684  -0.0395   0.6092   1.0000
   5.000   0.8029   0.01293   0.00682  -0.0386   0.5988   1.0000
   5.250   0.8270   0.01286   0.00683  -0.0378   0.5874   1.0000
   5.500   0.8511   0.01276   0.00681  -0.0369   0.5756   1.0000
   5.750   0.8751   0.01267   0.00678  -0.0360   0.5621   1.0000
   6.000   0.8988   0.01259   0.00677  -0.0350   0.5461   1.0000
   6.250   0.9221   0.01253   0.00673  -0.0340   0.5270   1.0000
   6.500   0.9446   0.01257   0.00684  -0.0329   0.5026   1.0000
   6.750   0.9663   0.01271   0.00696  -0.0317   0.4736   1.0000
   7.000   0.9862   0.01300   0.00716  -0.0303   0.4368   1.0000
   7.250   1.0038   0.01352   0.00752  -0.0286   0.3941   1.0000
   7.500   1.0180   0.01428   0.00806  -0.0266   0.3460   1.0000
   7.750   1.0292   0.01523   0.00877  -0.0242   0.2967   1.0000
   8.000   1.0390   0.01623   0.00954  -0.0218   0.2503   1.0000
   8.250   1.0473   0.01725   0.01037  -0.0191   0.2115   1.0000
   8.500   1.0550   0.01825   0.01123  -0.0164   0.1776   1.0000
   8.750   1.0605   0.01930   0.01213  -0.0134   0.1488   1.0000
   9.000   1.0638   0.02039   0.01310  -0.0101   0.1243   1.0000
   9.250   1.0623   0.02153   0.01412  -0.0060   0.1050   1.0000
   9.500   1.0572   0.02275   0.01525  -0.0017   0.0905   1.0000
   9.750   1.0541   0.02420   0.01667   0.0017   0.0754   1.0000
  10.000   1.0508   0.02591   0.01832   0.0047   0.0643   1.0000
  10.250   1.0499   0.02765   0.02004   0.0072   0.0548   1.0000
  10.500   1.0531   0.02924   0.02169   0.0092   0.0480   1.0000
  10.750   1.0520   0.03124   0.02365   0.0114   0.0436   1.0000
  11.000   1.0568   0.03294   0.02544   0.0133   0.0405   1.0000
  11.250   1.0636   0.03447   0.02705   0.0147   0.0370   1.0000
  11.500   1.0679   0.03625   0.02882   0.0162   0.0342   1.0000
  11.750   1.0759   0.03813   0.03075   0.0180   0.0321   1.0000
  12.000   1.0861   0.03969   0.03246   0.0194   0.0304   1.0000
  12.250   1.0943   0.04137   0.03426   0.0206   0.0285   1.0000
  12.500   1.1009   0.04309   0.03607   0.0215   0.0268   1.0000
  12.750   1.1126   0.04586   0.03886   0.0233   0.0245   1.0000
  13.000   1.1178   0.04799   0.04121   0.0243   0.0240   1.0000
  13.250   1.1205   0.05049   0.04395   0.0253   0.0233   1.0000
  13.500   1.1219   0.05330   0.04700   0.0263   0.0229   1.0000
  13.750   1.1189   0.05649   0.05044   0.0270   0.0224   1.0000
  14.000   1.1125   0.06002   0.05422   0.0274   0.0219   1.0000
  14.250   1.1046   0.06370   0.05811   0.0275   0.0215   1.0000
  14.500   1.0973   0.06710   0.06168   0.0272   0.0208   1.0000
  14.750   1.0848   0.07158   0.06639   0.0266   0.0208   1.0000
  15.000   1.0760   0.07550   0.07043   0.0257   0.0202   1.0000
  15.250   1.0649   0.07995   0.07504   0.0243   0.0198   1.0000
  15.500   1.0533   0.08471   0.07992   0.0225   0.0194   1.0000
  15.750   1.0150   0.09478   0.09042   0.0181   0.0206   1.0000
  16.000   0.9834   0.10448   0.10038   0.0129   0.0214   1.0000
  16.250   0.9663   0.11183   0.10787   0.0086   0.0208   1.0000
  16.500   0.9228   0.12610   0.12234   0.0004   0.0233   1.0000
  16.750   0.8943   0.13809   0.13444  -0.0068   0.0237   1.0000
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