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E224 (10.17%) (e224-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: E224 (10.17%) (e224-il)
Reynolds number: 100,000
Max Cl/Cd: 51.19 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e224-il-100000.txt
Download as CSV file: xf-e224-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E224  (10.17%)                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.3753   0.12683   0.12193  -0.0189   1.0000   0.0997
 -11.500  -0.3942   0.12482   0.11997  -0.0225   1.0000   0.1024
 -11.250  -0.4149   0.12226   0.11748  -0.0266   1.0000   0.1030
 -11.000  -0.3737   0.11618   0.11134  -0.0220   1.0000   0.1069
 -10.750  -0.3694   0.11281   0.10798  -0.0224   1.0000   0.1108
 -10.500  -0.3826   0.10955   0.10478  -0.0252   1.0000   0.1155
 -10.250  -0.4124   0.10645   0.10178  -0.0303   1.0000   0.1167
 -10.000  -0.3757   0.10121   0.09649  -0.0259   1.0000   0.1201
  -9.750  -0.3702   0.09767   0.09296  -0.0259   1.0000   0.1237
  -9.500  -0.3884   0.09394   0.08931  -0.0291   1.0000   0.1295
  -9.250  -0.4036   0.08917   0.08464  -0.0318   1.0000   0.1314
  -9.000  -0.3826   0.08528   0.08071  -0.0292   1.0000   0.1341
  -8.750  -0.3795   0.08165   0.07711  -0.0291   1.0000   0.1385
  -8.500  -0.4751   0.08678   0.08203  -0.0288   1.0000   0.1348
  -8.250  -0.4754   0.08341   0.07872  -0.0293   1.0000   0.1380
  -7.500  -0.5704   0.05509   0.05009  -0.0470   1.0000   0.0728
  -7.250  -0.5831   0.04739   0.04178  -0.0463   1.0000   0.0605
  -7.000  -0.5803   0.04277   0.03685  -0.0448   1.0000   0.0573
  -6.750  -0.5792   0.03698   0.03004  -0.0426   1.0000   0.0523
  -6.500  -0.5649   0.03442   0.02693  -0.0406   1.0000   0.0512
  -6.250  -0.5496   0.03152   0.02363  -0.0390   1.0000   0.0512
  -6.000  -0.5330   0.02846   0.02030  -0.0377   1.0000   0.0527
  -5.750  -0.5148   0.02682   0.01856  -0.0364   1.0000   0.0567
  -5.500  -0.4945   0.02510   0.01652  -0.0349   1.0000   0.0605
  -5.250  -0.4731   0.02311   0.01425  -0.0334   1.0000   0.0642
  -5.000  -0.4529   0.02169   0.01286  -0.0322   1.0000   0.0731
  -4.750  -0.4324   0.02024   0.01145  -0.0310   1.0000   0.0856
  -4.500  -0.4122   0.01891   0.01022  -0.0298   1.0000   0.1085
  -4.250  -0.3915   0.01754   0.00912  -0.0288   1.0000   0.1593
  -4.000  -0.3714   0.01638   0.00846  -0.0281   1.0000   0.2423
  -3.750  -0.3515   0.01571   0.00818  -0.0272   1.0000   0.3264
  -3.500  -0.3317   0.01528   0.00803  -0.0261   1.0000   0.4017
  -3.250  -0.3124   0.01498   0.00794  -0.0247   1.0000   0.4683
  -3.000  -0.2935   0.01477   0.00793  -0.0232   1.0000   0.5308
  -2.750  -0.2754   0.01464   0.00798  -0.0214   1.0000   0.5899
  -2.500  -0.2582   0.01457   0.00808  -0.0193   1.0000   0.6461
  -2.250  -0.2427   0.01456   0.00821  -0.0169   1.0000   0.7006
  -2.000  -0.2289   0.01459   0.00836  -0.0140   1.0000   0.7553
  -1.750  -0.2166   0.01466   0.00853  -0.0107   1.0000   0.8113
  -1.500  -0.1818   0.01494   0.00889  -0.0113   0.9904   0.8817
  -1.250  -0.1158   0.01524   0.00908  -0.0184   0.9844   0.9614
  -1.000  -0.0500   0.01539   0.00900  -0.0271   0.9765   1.0000
  -0.750  -0.0030   0.01560   0.00899  -0.0321   0.9658   1.0000
  -0.500   0.0474   0.01583   0.00905  -0.0373   0.9564   1.0000
  -0.250   0.0898   0.01595   0.00903  -0.0408   0.9444   1.0000
   0.000   0.1323   0.01605   0.00903  -0.0442   0.9326   1.0000
   0.250   0.1769   0.01612   0.00902  -0.0477   0.9215   1.0000
   0.500   0.2321   0.01606   0.00891  -0.0529   0.9136   1.0000
   0.750   0.2747   0.01598   0.00880  -0.0558   0.9013   1.0000
   1.000   0.3169   0.01586   0.00867  -0.0584   0.8891   1.0000
   1.250   0.3578   0.01570   0.00851  -0.0605   0.8768   1.0000
   1.500   0.3973   0.01549   0.00831  -0.0622   0.8641   1.0000
   1.750   0.4338   0.01529   0.00812  -0.0632   0.8504   1.0000
   2.000   0.4668   0.01511   0.00797  -0.0635   0.8353   1.0000
   2.250   0.4975   0.01496   0.00782  -0.0633   0.8192   1.0000
   2.500   0.5270   0.01482   0.00768  -0.0628   0.8023   1.0000
   2.750   0.5561   0.01469   0.00757  -0.0621   0.7851   1.0000
   3.000   0.5815   0.01467   0.00755  -0.0610   0.7653   1.0000
   3.250   0.6073   0.01465   0.00753  -0.0598   0.7447   1.0000
   3.500   0.6336   0.01465   0.00750  -0.0587   0.7239   1.0000
   3.750   0.6581   0.01471   0.00758  -0.0574   0.7006   1.0000
   4.000   0.6826   0.01480   0.00765  -0.0561   0.6765   1.0000
   4.250   0.7074   0.01490   0.00771  -0.0549   0.6518   1.0000
   4.500   0.7316   0.01505   0.00781  -0.0536   0.6253   1.0000
   4.750   0.7549   0.01524   0.00799  -0.0522   0.5968   1.0000
   5.000   0.7778   0.01547   0.00818  -0.0508   0.5670   1.0000
   5.250   0.7997   0.01575   0.00843  -0.0493   0.5345   1.0000
   5.500   0.8214   0.01608   0.00871  -0.0477   0.5007   1.0000
   5.750   0.8426   0.01646   0.00901  -0.0462   0.4658   1.0000
   6.000   0.8626   0.01690   0.00940  -0.0446   0.4272   1.0000
   6.250   0.8819   0.01744   0.00983  -0.0429   0.3873   1.0000
   6.500   0.9003   0.01808   0.01035  -0.0411   0.3457   1.0000
   6.750   0.9176   0.01885   0.01100  -0.0394   0.3027   1.0000
   7.000   0.9337   0.01977   0.01173  -0.0375   0.2587   1.0000
   7.250   0.9487   0.02085   0.01260  -0.0356   0.2156   1.0000
   7.500   0.9629   0.02206   0.01359  -0.0337   0.1758   1.0000
   7.750   0.9765   0.02343   0.01476  -0.0318   0.1420   1.0000
   8.000   0.9904   0.02507   0.01623  -0.0299   0.1148   1.0000
   8.250   1.0056   0.02684   0.01795  -0.0280   0.0937   1.0000
   8.500   1.0239   0.02882   0.01994  -0.0266   0.0805   1.0000
   8.750   1.0451   0.03108   0.02216  -0.0257   0.0716   1.0000
   9.000   1.0641   0.03281   0.02396  -0.0246   0.0640   1.0000
   9.250   1.0875   0.03594   0.02730  -0.0240   0.0598   1.0000
   9.500   1.1051   0.03831   0.03003  -0.0225   0.0560   1.0000
   9.750   1.1213   0.04049   0.03227  -0.0214   0.0518   1.0000
  10.000   1.1351   0.04513   0.03718  -0.0204   0.0499   1.0000
  10.250   1.1396   0.04829   0.04086  -0.0178   0.0493   1.0000
  10.500   1.1386   0.05165   0.04472  -0.0150   0.0486   1.0000
  10.750   1.1324   0.05510   0.04864  -0.0121   0.0480   1.0000
  11.000   1.1206   0.05847   0.05238  -0.0091   0.0475   1.0000
  11.250   1.1041   0.06184   0.05603  -0.0060   0.0474   1.0000
  11.500   1.0853   0.06560   0.06004  -0.0040   0.0475   1.0000
  11.750   1.0635   0.06972   0.06440  -0.0032   0.0475   1.0000
  12.000   1.0417   0.07457   0.06945  -0.0037   0.0479   1.0000
  12.250   1.0198   0.08022   0.07522  -0.0055   0.0485   1.0000
  12.500   0.9987   0.08651   0.08164  -0.0083   0.0491   1.0000
  12.750   0.9780   0.09357   0.08880  -0.0120   0.0496   1.0000
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