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E222 (10.17%) (e222-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: E222 (10.17%) (e222-il)
Reynolds number: 500,000
Max Cl/Cd: 101.71 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e222-il-500000.txt
Download as CSV file: xf-e222-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3580   0.08272   0.08059  -0.0375   1.0000   0.0272
  -9.500  -0.3626   0.07860   0.07649  -0.0381   1.0000   0.0281
  -9.250  -0.3699   0.07406   0.07198  -0.0388   1.0000   0.0287
  -9.000  -0.3807   0.06895   0.06691  -0.0399   1.0000   0.0296
  -8.750  -0.3941   0.06379   0.06178  -0.0408   1.0000   0.0299
  -8.250  -0.5668   0.05544   0.05329  -0.0507   1.0000   0.0257
  -8.000  -0.5791   0.05224   0.05000  -0.0497   1.0000   0.0259
  -7.750  -0.5577   0.04808   0.04568  -0.0552   0.9969   0.0268
  -6.750  -0.4615   0.02060   0.01547  -0.0708   0.9830   0.0192
  -6.500  -0.4331   0.01901   0.01369  -0.0714   0.9789   0.0195
  -6.250  -0.4007   0.01724   0.01165  -0.0726   0.9762   0.0191
  -6.000  -0.3668   0.01585   0.01011  -0.0740   0.9741   0.0191
  -5.750  -0.3317   0.01467   0.00883  -0.0758   0.9724   0.0194
  -5.500  -0.2951   0.01372   0.00781  -0.0778   0.9711   0.0200
  -5.250  -0.2685   0.01298   0.00701  -0.0777   0.9649   0.0206
  -5.000  -0.2338   0.01229   0.00625  -0.0793   0.9621   0.0213
  -4.750  -0.1971   0.01167   0.00558  -0.0812   0.9601   0.0222
  -4.500  -0.1591   0.01118   0.00503  -0.0834   0.9585   0.0238
  -4.250  -0.1286   0.01060   0.00436  -0.0840   0.9535   0.0254
  -4.000  -0.0939   0.01011   0.00385  -0.0853   0.9498   0.0294
  -3.750  -0.0577   0.00938   0.00333  -0.0872   0.9471   0.0743
  -3.500  -0.0217   0.00864   0.00296  -0.0893   0.9446   0.1673
  -3.250   0.0069   0.00818   0.00274  -0.0896   0.9376   0.2359
  -3.000   0.0405   0.00773   0.00253  -0.0910   0.9326   0.3048
  -2.750   0.0724   0.00741   0.00234  -0.0919   0.9263   0.3562
  -2.500   0.1033   0.00712   0.00220  -0.0925   0.9186   0.4098
  -2.250   0.1332   0.00682   0.00210  -0.0929   0.9099   0.4775
  -2.000   0.1643   0.00658   0.00199  -0.0935   0.9015   0.5340
  -1.750   0.1921   0.00644   0.00193  -0.0933   0.8902   0.5711
  -1.500   0.2205   0.00634   0.00187  -0.0933   0.8789   0.6051
  -1.250   0.2486   0.00624   0.00182  -0.0931   0.8673   0.6387
  -1.000   0.2763   0.00617   0.00179  -0.0929   0.8551   0.6710
  -0.750   0.3036   0.00612   0.00177  -0.0925   0.8422   0.7015
  -0.500   0.3304   0.00609   0.00176  -0.0921   0.8287   0.7303
  -0.250   0.3568   0.00608   0.00176  -0.0915   0.8145   0.7575
   0.000   0.3829   0.00608   0.00177  -0.0909   0.8000   0.7841
   0.250   0.4084   0.00609   0.00180  -0.0901   0.7851   0.8092
   0.500   0.4336   0.00611   0.00183  -0.0893   0.7697   0.8329
   0.750   0.4583   0.00615   0.00186  -0.0883   0.7536   0.8563
   1.000   0.4820   0.00619   0.00190  -0.0872   0.7372   0.8782
   1.250   0.5052   0.00623   0.00193  -0.0858   0.7202   0.9012
   1.500   0.5268   0.00627   0.00196  -0.0842   0.7035   0.9247
   1.750   0.5497   0.00630   0.00196  -0.0828   0.6863   0.9507
   2.000   0.5821   0.00637   0.00196  -0.0836   0.6677   0.9770
   2.250   0.6162   0.00646   0.00200  -0.0850   0.6471   1.0000
   2.500   0.6422   0.00662   0.00206  -0.0847   0.6269   1.0000
   2.750   0.6684   0.00679   0.00214  -0.0844   0.6059   1.0000
   3.000   0.6943   0.00696   0.00224  -0.0840   0.5842   1.0000
   3.250   0.7202   0.00715   0.00236  -0.0837   0.5620   1.0000
   3.500   0.7456   0.00737   0.00248  -0.0832   0.5382   1.0000
   3.750   0.7711   0.00759   0.00262  -0.0828   0.5130   1.0000
   4.000   0.7964   0.00783   0.00277  -0.0823   0.4881   1.0000
   4.250   0.8214   0.00810   0.00295  -0.0818   0.4622   1.0000
   5.000   0.8948   0.00905   0.00358  -0.0801   0.3723   1.0000
   5.250   0.9188   0.00943   0.00385  -0.0795   0.3401   1.0000
   5.500   0.9419   0.00988   0.00414  -0.0787   0.3035   1.0000
   5.750   0.9642   0.01042   0.00447  -0.0779   0.2608   1.0000
   6.000   0.9871   0.01091   0.00481  -0.0772   0.2258   1.0000
   6.250   1.0095   0.01145   0.00520  -0.0764   0.1919   1.0000
   6.500   1.0314   0.01204   0.00562  -0.0756   0.1569   1.0000
   6.750   1.0529   0.01267   0.00607  -0.0747   0.1242   1.0000
   7.000   1.0743   0.01329   0.00655  -0.0737   0.0970   1.0000
   7.250   1.0958   0.01389   0.00706  -0.0728   0.0749   1.0000
   7.500   1.1154   0.01468   0.00767  -0.0717   0.0484   1.0000
   7.750   1.1312   0.01585   0.00863  -0.0698   0.0196   1.0000
   8.000   1.1499   0.01671   0.00950  -0.0683   0.0151   1.0000
   8.250   1.1706   0.01733   0.01019  -0.0671   0.0136   1.0000
   8.500   1.1899   0.01805   0.01096  -0.0658   0.0123   1.0000
   8.750   1.2057   0.01905   0.01206  -0.0640   0.0114   1.0000
   9.000   1.2205   0.02006   0.01318  -0.0620   0.0110   1.0000
   9.250   1.2362   0.02093   0.01414  -0.0602   0.0107   1.0000
   9.500   1.2493   0.02188   0.01518  -0.0579   0.0104   1.0000
   9.750   1.2603   0.02285   0.01624  -0.0553   0.0101   1.0000
  10.000   1.2698   0.02391   0.01740  -0.0527   0.0098   1.0000
  10.250   1.2782   0.02509   0.01868  -0.0499   0.0096   1.0000
  10.500   1.2862   0.02633   0.02004  -0.0473   0.0094   1.0000
  10.750   1.2932   0.02769   0.02150  -0.0448   0.0092   1.0000
  11.000   1.2997   0.02915   0.02307  -0.0424   0.0091   1.0000
  11.250   1.3052   0.03078   0.02479  -0.0401   0.0089   1.0000
  11.500   1.3103   0.03255   0.02669  -0.0379   0.0088   1.0000
  11.750   1.3148   0.03447   0.02874  -0.0359   0.0087   1.0000
  12.000   1.3182   0.03660   0.03100  -0.0340   0.0086   1.0000
  12.250   1.3210   0.03888   0.03344  -0.0323   0.0086   1.0000
  12.500   1.3223   0.04142   0.03615  -0.0308   0.0086   1.0000
  12.750   1.3221   0.04418   0.03909  -0.0294   0.0086   1.0000
  13.000   1.3202   0.04716   0.04226  -0.0283   0.0087   1.0000
  13.250   1.3158   0.05051   0.04581  -0.0276   0.0087   1.0000
  13.500   1.3100   0.05409   0.04959  -0.0272   0.0086   1.0000
  13.750   1.3001   0.05845   0.05419  -0.0273   0.0087   1.0000
  14.000   1.2920   0.06258   0.05848  -0.0280   0.0086   1.0000
  14.250   1.2790   0.06777   0.06389  -0.0293   0.0087   1.0000
  14.500   1.2678   0.07284   0.06912  -0.0311   0.0086   1.0000
  14.750   1.2490   0.07971   0.07625  -0.0340   0.0088   1.0000
  15.000   1.2303   0.08696   0.08372  -0.0376   0.0089   1.0000
  15.250   1.2009   0.09702   0.09407  -0.0435   0.0091   1.0000
  15.500   1.1667   0.10914   0.10647  -0.0510   0.0094   1.0000
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