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E201 (11.88%) (e201-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: E201 (11.88%) (e201-il)
Reynolds number: 500,000
Max Cl/Cd: 111.97 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e201-il-500000.txt
Download as CSV file: xf-e201-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E201  (11.88%)                                  
  
 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  -0.3968   0.08782   0.08560  -0.0438   1.0000   0.0270
  -9.500  -0.3982   0.08438   0.08219  -0.0449   1.0000   0.0279
  -7.750  -0.4629   0.02489   0.02028  -0.0828   0.9692   0.0189
  -7.500  -0.4337   0.02326   0.01841  -0.0838   0.9615   0.0187
  -7.250  -0.4068   0.02059   0.01547  -0.0846   0.9530   0.0184
  -7.000  -0.3765   0.01893   0.01357  -0.0855   0.9438   0.0185
  -6.750  -0.3482   0.01751   0.01195  -0.0859   0.9309   0.0186
  -6.500  -0.3210   0.01565   0.00989  -0.0861   0.9161   0.0189
  -6.250  -0.2956   0.01420   0.00829  -0.0859   0.8987   0.0196
  -6.000  -0.2706   0.01340   0.00737  -0.0854   0.8794   0.0202
  -5.750  -0.2461   0.01275   0.00659  -0.0848   0.8608   0.0207
  -5.500  -0.2217   0.01221   0.00592  -0.0841   0.8433   0.0213
  -5.250  -0.1971   0.01176   0.00532  -0.0834   0.8271   0.0222
  -5.000  -0.1720   0.01136   0.00480  -0.0828   0.8122   0.0231
  -4.750  -0.1465   0.01104   0.00434  -0.0824   0.7985   0.0241
  -4.500  -0.1213   0.01058   0.00378  -0.0818   0.7857   0.0265
  -4.250  -0.0951   0.01032   0.00344  -0.0815   0.7741   0.0305
  -4.000  -0.0700   0.00980   0.00302  -0.0810   0.7637   0.0613
  -3.750  -0.0447   0.00936   0.00275  -0.0807   0.7533   0.1175
  -3.500  -0.0187   0.00904   0.00257  -0.0805   0.7437   0.1644
  -3.250   0.0073   0.00877   0.00240  -0.0803   0.7352   0.2168
  -3.000   0.0332   0.00842   0.00227  -0.0801   0.7264   0.2847
  -2.750   0.0590   0.00812   0.00218  -0.0799   0.7186   0.3607
  -2.500   0.0854   0.00794   0.00213  -0.0797   0.7107   0.4220
  -2.250   0.1123   0.00784   0.00209  -0.0795   0.7037   0.4652
  -2.000   0.1394   0.00776   0.00206  -0.0794   0.6963   0.4979
  -1.750   0.1665   0.00771   0.00203  -0.0792   0.6898   0.5300
  -1.500   0.1937   0.00763   0.00201  -0.0790   0.6829   0.5601
  -1.250   0.2209   0.00762   0.00199  -0.0789   0.6769   0.5852
  -1.000   0.2482   0.00755   0.00198  -0.0787   0.6703   0.6118
  -0.750   0.2752   0.00751   0.00198  -0.0785   0.6644   0.6402
  -0.500   0.3022   0.00747   0.00199  -0.0783   0.6586   0.6710
  -0.250   0.3288   0.00739   0.00201  -0.0779   0.6524   0.7047
   0.000   0.3550   0.00736   0.00203  -0.0775   0.6472   0.7435
   0.250   0.3806   0.00725   0.00208  -0.0769   0.6414   0.7875
   0.500   0.4054   0.00717   0.00213  -0.0760   0.6358   0.8370
   0.750   0.4296   0.00712   0.00219  -0.0749   0.6307   0.8915
   1.000   0.4614   0.00710   0.00224  -0.0754   0.6249   0.9434
   1.250   0.5038   0.00715   0.00226  -0.0785   0.6193   0.9752
   1.500   0.5481   0.00721   0.00229  -0.0821   0.6136   0.9923
   1.750   0.5850   0.00726   0.00231  -0.0842   0.6077   1.0000
   2.250   0.6342   0.00743   0.00242  -0.0829   0.5963   1.0000
   2.500   0.6590   0.00752   0.00247  -0.0824   0.5901   1.0000
   2.750   0.6842   0.00760   0.00254  -0.0818   0.5836   1.0000
   3.000   0.7095   0.00768   0.00262  -0.0813   0.5767   1.0000
   3.250   0.7351   0.00778   0.00270  -0.0809   0.5702   1.0000
   3.500   0.7607   0.00785   0.00277  -0.0804   0.5624   1.0000
   3.750   0.7864   0.00795   0.00286  -0.0800   0.5549   1.0000
   4.000   0.8122   0.00804   0.00296  -0.0796   0.5470   1.0000
   4.250   0.8381   0.00814   0.00306  -0.0793   0.5390   1.0000
   4.500   0.8638   0.00824   0.00316  -0.0788   0.5304   1.0000
   4.750   0.8896   0.00833   0.00329  -0.0785   0.5208   1.0000
   5.000   0.9152   0.00846   0.00341  -0.0780   0.5112   1.0000
   5.250   0.9406   0.00859   0.00354  -0.0776   0.5006   1.0000
   5.500   0.9660   0.00871   0.00369  -0.0771   0.4885   1.0000
   5.750   0.9903   0.00887   0.00384  -0.0765   0.4716   1.0000
   6.000   1.0144   0.00906   0.00401  -0.0758   0.4505   1.0000
   6.250   1.0370   0.00933   0.00420  -0.0749   0.4224   1.0000
   6.500   1.0590   0.00968   0.00445  -0.0739   0.3911   1.0000
   6.750   1.0772   0.01027   0.00482  -0.0724   0.3413   1.0000
   7.000   1.0917   0.01117   0.00537  -0.0704   0.2754   1.0000
   7.250   1.1065   0.01205   0.00598  -0.0684   0.2229   1.0000
   7.500   1.1210   0.01294   0.00661  -0.0665   0.1744   1.0000
   7.750   1.1357   0.01378   0.00724  -0.0646   0.1357   1.0000
   8.000   1.1507   0.01456   0.00786  -0.0627   0.1056   1.0000
   8.250   1.1641   0.01539   0.00853  -0.0606   0.0780   1.0000
   8.500   1.1745   0.01635   0.00931  -0.0580   0.0489   1.0000
   8.750   1.1770   0.01753   0.01029  -0.0541   0.0235   1.0000
   9.000   1.1852   0.01840   0.01115  -0.0510   0.0174   1.0000
   9.250   1.1928   0.01935   0.01213  -0.0481   0.0148   1.0000
   9.500   1.2047   0.02009   0.01295  -0.0459   0.0140   1.0000
   9.750   1.2146   0.02097   0.01390  -0.0436   0.0133   1.0000
  10.000   1.2236   0.02193   0.01493  -0.0413   0.0125   1.0000
  10.250   1.2305   0.02307   0.01615  -0.0390   0.0121   1.0000
  10.500   1.2340   0.02451   0.01766  -0.0365   0.0116   1.0000
  10.750   1.2320   0.02645   0.01971  -0.0339   0.0112   1.0000
  11.000   1.2357   0.02811   0.02145  -0.0320   0.0110   1.0000
  11.250   1.2418   0.02966   0.02310  -0.0306   0.0109   1.0000
  11.500   1.2461   0.03146   0.02500  -0.0291   0.0106   1.0000
  11.750   1.2503   0.03333   0.02696  -0.0279   0.0105   1.0000
  12.000   1.2538   0.03535   0.02907  -0.0267   0.0103   1.0000
  12.250   1.2567   0.03749   0.03132  -0.0256   0.0101   1.0000
  12.500   1.2596   0.03971   0.03363  -0.0247   0.0099   1.0000
  12.750   1.2630   0.04194   0.03595  -0.0238   0.0098   1.0000
  13.000   1.2666   0.04419   0.03830  -0.0230   0.0097   1.0000
  13.250   1.2703   0.04650   0.04071  -0.0223   0.0097   1.0000
  13.500   1.2741   0.04883   0.04314  -0.0218   0.0094   1.0000
  13.750   1.2778   0.05125   0.04566  -0.0213   0.0093   1.0000
  14.000   1.2811   0.05376   0.04829  -0.0210   0.0092   1.0000
  14.250   1.2836   0.05638   0.05098  -0.0210   0.0090   1.0000
  14.500   1.2856   0.05924   0.05399  -0.0206   0.0090   1.0000
  14.750   1.2872   0.06209   0.05692  -0.0209   0.0088   1.0000
  15.000   1.2873   0.06532   0.06028  -0.0209   0.0087   1.0000
  15.250   1.2866   0.06872   0.06381  -0.0213   0.0087   1.0000
  15.500   1.2850   0.07232   0.06755  -0.0218   0.0086   1.0000
  15.750   1.2812   0.07637   0.07176  -0.0226   0.0086   1.0000
  16.000   1.2756   0.08079   0.07636  -0.0237   0.0086   1.0000
  16.250   1.2684   0.08558   0.08132  -0.0252   0.0086   1.0000
  16.500   1.2596   0.09082   0.08673  -0.0271   0.0086   1.0000
  16.750   1.2477   0.09681   0.09295  -0.0295   0.0088   1.0000
  17.000   1.2349   0.10315   0.09949  -0.0324   0.0088   1.0000
  17.250   1.2191   0.11036   0.10692  -0.0359   0.0089   1.0000
  17.500   1.1994   0.11872   0.11551  -0.0404   0.0090   1.0000
  17.750   1.1661   0.13070   0.12782  -0.0476   0.0093   1.0000
  18.000   1.1452   0.14042   0.13773  -0.0537   0.0094   1.0000
  18.250   1.1154   0.15327   0.15081  -0.0619   0.0095   1.0000
  18.500   1.0733   0.17108   0.16886  -0.0733   0.0101   1.0000
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