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E203 (13.64%) (e203-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: E203 (13.64%) (e203-il)
Reynolds number: 50,000
Max Cl/Cd: 31.22 at α=8.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e203-il-50000-n5.txt
Download as CSV file: xf-e203-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E203  (13.64%)                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.4365   0.10399   0.09666  -0.0477   1.0000   0.0542
 -11.000  -0.4441   0.09830   0.09105  -0.0500   1.0000   0.0538
 -10.750  -0.4553   0.09179   0.08462  -0.0529   1.0000   0.0533
 -10.500  -0.4726   0.08438   0.07729  -0.0567   1.0000   0.0527
 -10.250  -0.4987   0.07648   0.06943  -0.0614   1.0000   0.0519
 -10.000  -0.5300   0.06952   0.06247  -0.0655   1.0000   0.0510
  -9.750  -0.5620   0.06450   0.05742  -0.0672   1.0000   0.0504
  -9.500  -0.5913   0.06098   0.05386  -0.0660   1.0000   0.0500
  -9.250  -0.6116   0.05758   0.05031  -0.0644   1.0000   0.0499
  -9.000  -0.6258   0.05442   0.04697  -0.0625   1.0000   0.0500
  -8.750  -0.6344   0.05148   0.04381  -0.0604   1.0000   0.0503
  -8.500  -0.6385   0.04872   0.04080  -0.0582   1.0000   0.0507
  -8.250  -0.6389   0.04613   0.03794  -0.0561   1.0000   0.0514
  -8.000  -0.6360   0.04375   0.03528  -0.0539   1.0000   0.0523
  -7.750  -0.6304   0.04154   0.03278  -0.0518   1.0000   0.0534
  -7.500  -0.6224   0.03956   0.03050  -0.0497   1.0000   0.0548
  -7.250  -0.6131   0.03787   0.02840  -0.0476   1.0000   0.0571
  -7.000  -0.6034   0.03647   0.02710  -0.0458   1.0000   0.0598
  -6.750  -0.5814   0.03504   0.02553  -0.0460   0.9962   0.0642
  -6.500  -0.5470   0.03332   0.02339  -0.0477   0.9883   0.0696
  -6.250  -0.5151   0.03176   0.02188  -0.0495   0.9799   0.0761
  -6.000  -0.4827   0.03029   0.02034  -0.0515   0.9711   0.0900
  -5.750  -0.4537   0.02883   0.01889  -0.0531   0.9609   0.1118
  -5.500  -0.4244   0.02736   0.01757  -0.0550   0.9513   0.1527
  -5.250  -0.3930   0.02588   0.01648  -0.0574   0.9427   0.2164
  -5.000  -0.3661   0.02490   0.01582  -0.0584   0.9321   0.2846
  -4.750  -0.3369   0.02455   0.01573  -0.0590   0.9224   0.3558
  -4.500  -0.3022   0.02457   0.01569  -0.0603   0.9144   0.4171
  -4.250  -0.2747   0.02464   0.01563  -0.0602   0.9039   0.4579
  -4.000  -0.2431   0.02470   0.01553  -0.0607   0.8955   0.4926
  -3.750  -0.2111   0.02471   0.01539  -0.0612   0.8873   0.5221
  -3.500  -0.1826   0.02474   0.01529  -0.0611   0.8784   0.5461
  -3.250  -0.1486   0.02466   0.01506  -0.0619   0.8716   0.5698
  -3.000  -0.1223   0.02464   0.01493  -0.0614   0.8622   0.5892
  -2.750  -0.0882   0.02451   0.01464  -0.0623   0.8560   0.6097
  -2.500  -0.0633   0.02447   0.01447  -0.0618   0.8464   0.6269
  -2.250  -0.0290   0.02432   0.01420  -0.0627   0.8406   0.6437
  -2.000  -0.0057   0.02432   0.01411  -0.0619   0.8309   0.6589
  -1.750   0.0286   0.02415   0.01382  -0.0628   0.8255   0.6748
  -1.500   0.0509   0.02418   0.01379  -0.0619   0.8156   0.6895
  -1.250   0.0836   0.02405   0.01356  -0.0625   0.8099   0.7047
  -1.000   0.1062   0.02410   0.01357  -0.0617   0.8007   0.7194
  -0.750   0.1385   0.02397   0.01337  -0.0623   0.7951   0.7347
  -0.500   0.1599   0.02407   0.01346  -0.0613   0.7860   0.7501
  -0.250   0.1926   0.02393   0.01328  -0.0619   0.7810   0.7668
   0.000   0.2120   0.02410   0.01347  -0.0606   0.7715   0.7844
   0.250   0.2441   0.02399   0.01334  -0.0611   0.7665   0.8047
   0.500   0.2638   0.02419   0.01360  -0.0598   0.7575   0.8267
   0.750   0.2975   0.02410   0.01352  -0.0606   0.7522   0.8525
   1.000   0.3252   0.02433   0.01381  -0.0609   0.7440   0.8831
   1.250   0.3715   0.02430   0.01379  -0.0644   0.7386   0.9172
   1.500   0.4188   0.02447   0.01397  -0.0688   0.7315   0.9609
   1.750   0.4583   0.02463   0.01408  -0.0720   0.7248   1.0000
   2.000   0.4780   0.02500   0.01436  -0.0714   0.7173   1.0000
   2.250   0.5009   0.02536   0.01466  -0.0712   0.7101   1.0000
   2.500   0.5246   0.02576   0.01502  -0.0710   0.7032   1.0000
   2.750   0.5469   0.02622   0.01545  -0.0706   0.6956   1.0000
   3.000   0.5730   0.02659   0.01579  -0.0706   0.6893   1.0000
   3.250   0.5929   0.02717   0.01638  -0.0698   0.6811   1.0000
   3.500   0.6216   0.02746   0.01670  -0.0701   0.6754   1.0000
   3.750   0.6388   0.02818   0.01745  -0.0689   0.6664   1.0000
   4.000   0.6681   0.02844   0.01775  -0.0691   0.6606   1.0000
   4.250   0.6845   0.02921   0.01858  -0.0679   0.6514   1.0000
   4.500   0.7101   0.02961   0.01907  -0.0676   0.6444   1.0000
   4.750   0.7310   0.03018   0.01972  -0.0668   0.6357   1.0000
   5.000   0.7505   0.03082   0.02044  -0.0658   0.6268   1.0000
   5.250   0.7796   0.03098   0.02070  -0.0657   0.6194   1.0000
   5.500   0.7946   0.03177   0.02163  -0.0641   0.6087   1.0000
   5.750   0.8275   0.03169   0.02165  -0.0643   0.6015   1.0000
   6.000   0.8452   0.03227   0.02237  -0.0629   0.5904   1.0000
   6.250   0.8616   0.03290   0.02312  -0.0613   0.5790   1.0000
   6.500   0.8860   0.03306   0.02346  -0.0604   0.5685   1.0000
   6.750   0.9206   0.03260   0.02316  -0.0603   0.5587   1.0000
   7.000   0.9378   0.03296   0.02367  -0.0585   0.5452   1.0000
   7.250   0.9571   0.03312   0.02399  -0.0568   0.5312   1.0000
   7.500   0.9779   0.03310   0.02417  -0.0552   0.5165   1.0000
   7.750   1.0001   0.03290   0.02413  -0.0535   0.5007   1.0000
   8.000   1.0144   0.03307   0.02446  -0.0511   0.4830   1.0000
   8.250   1.0234   0.03347   0.02501  -0.0482   0.4636   1.0000
   8.500   1.0396   0.03330   0.02495  -0.0457   0.4427   1.0000
   8.750   1.0438   0.03393   0.02570  -0.0424   0.4196   1.0000
   9.000   1.0529   0.03431   0.02618  -0.0396   0.3933   1.0000
   9.250   1.0598   0.03495   0.02684  -0.0368   0.3632   1.0000
   9.500   1.0655   0.03580   0.02763  -0.0342   0.3303   1.0000
   9.750   1.0690   0.03699   0.02863  -0.0316   0.2963   1.0000
  10.000   1.0682   0.03876   0.03024  -0.0293   0.2640   1.0000
  10.250   1.0661   0.04088   0.03218  -0.0273   0.2355   1.0000
  10.500   1.0628   0.04329   0.03441  -0.0256   0.2105   1.0000
  10.750   1.0599   0.04589   0.03693  -0.0243   0.1876   1.0000
  11.000   1.0570   0.04859   0.03950  -0.0232   0.1690   1.0000
  11.250   1.0552   0.05138   0.04224  -0.0223   0.1507   1.0000
  11.500   1.0540   0.05420   0.04506  -0.0215   0.1350   1.0000
  11.750   1.0530   0.05710   0.04794  -0.0209   0.1208   1.0000
  12.000   1.0525   0.06005   0.05086  -0.0205   0.1083   1.0000
  12.250   1.0519   0.06307   0.05387  -0.0202   0.0971   1.0000
  12.500   1.0508   0.06619   0.05691  -0.0200   0.0874   1.0000
  12.750   1.0507   0.06941   0.06026  -0.0200   0.0777   1.0000
  13.000   1.0516   0.07262   0.06358  -0.0200   0.0697   1.0000
  13.250   1.0507   0.07591   0.06682  -0.0203   0.0636   1.0000
  13.500   1.0536   0.07922   0.07038  -0.0203   0.0577   1.0000
  13.750   1.0540   0.08258   0.07376  -0.0207   0.0533   1.0000
  14.000   1.0568   0.08601   0.07737  -0.0208   0.0496   1.0000
  14.250   1.0577   0.08990   0.08154  -0.0213   0.0467   1.0000
  14.500   1.0571   0.09388   0.08573  -0.0221   0.0445   1.0000
  14.750   1.0577   0.09746   0.08934  -0.0230   0.0423   1.0000
  15.000   1.0535   0.10225   0.09430  -0.0245   0.0409   1.0000
  15.250   1.0430   0.10840   0.10078  -0.0271   0.0401   1.0000
  15.500   1.0291   0.11544   0.10811  -0.0305   0.0395   1.0000
  15.750   1.0137   0.12315   0.11606  -0.0346   0.0394   1.0000
  16.000   0.9948   0.13217   0.12531  -0.0398   0.0394   1.0000
  16.250   0.9734   0.14262   0.13590  -0.0461   0.0398   1.0000
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