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E201 (11.88%) (e201-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: E201 (11.88%) (e201-il)
Reynolds number: 100,000
Max Cl/Cd: 56.67 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e201-il-100000.txt
Download as CSV file: xf-e201-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3619   0.10893   0.10390  -0.0359   1.0000   0.1124
  -9.750  -0.3829   0.10669   0.10179  -0.0403   1.0000   0.1171
  -9.500  -0.4125   0.10437   0.09966  -0.0455   1.0000   0.1178
  -9.250  -0.3651   0.09908   0.09424  -0.0386   1.0000   0.1217
  -9.000  -0.3608   0.09627   0.09147  -0.0384   1.0000   0.1258
  -8.750  -0.3898   0.09397   0.08935  -0.0424   1.0000   0.1313
  -8.500  -0.3999   0.09014   0.08564  -0.0429   1.0000   0.1331
  -8.250  -0.3755   0.08707   0.08254  -0.0395   1.0000   0.1365
  -8.000  -0.3774   0.08456   0.08010  -0.0387   1.0000   0.1403
  -7.750  -0.4128   0.08278   0.07854  -0.0388   1.0000   0.1449
  -7.500  -0.4875   0.08079   0.07669  -0.0434   1.0000   0.1466
  -7.250  -0.4500   0.07759   0.07362  -0.0360   1.0000   0.1489
  -7.000  -0.4569   0.07614   0.07225  -0.0319   1.0000   0.1508
  -6.750  -0.4747   0.07487   0.07107  -0.0288   1.0000   0.1527
  -6.500  -0.4946   0.07321   0.06948  -0.0270   1.0000   0.1555
  -6.250  -0.4849   0.04594   0.04054  -0.0543   0.9856   0.0737
  -6.000  -0.4544   0.03885   0.03218  -0.0580   0.9767   0.0630
  -5.750  -0.4182   0.03442   0.02727  -0.0614   0.9708   0.0617
  -5.500  -0.3845   0.03154   0.02383  -0.0633   0.9618   0.0621
  -5.250  -0.3466   0.02890   0.02068  -0.0658   0.9553   0.0645
  -5.000  -0.3109   0.02673   0.01832  -0.0676   0.9473   0.0667
  -4.750  -0.2716   0.02502   0.01642  -0.0697   0.9407   0.0704
  -4.500  -0.2345   0.02368   0.01483  -0.0711   0.9328   0.0763
  -4.250  -0.1978   0.02215   0.01345  -0.0731   0.9262   0.0915
  -4.000  -0.1651   0.02045   0.01209  -0.0742   0.9182   0.1375
  -3.750  -0.1316   0.01894   0.01126  -0.0761   0.9113   0.2600
  -3.500  -0.0998   0.01815   0.01113  -0.0772   0.9034   0.4035
  -3.250  -0.0670   0.01788   0.01106  -0.0778   0.8961   0.4980
  -3.000  -0.0350   0.01770   0.01094  -0.0781   0.8885   0.5659
  -2.750  -0.0057   0.01758   0.01089  -0.0777   0.8808   0.6186
  -2.500   0.0247   0.01742   0.01078  -0.0775   0.8735   0.6666
  -2.250   0.0518   0.01732   0.01070  -0.0766   0.8658   0.7088
  -2.000   0.0804   0.01717   0.01058  -0.0759   0.8586   0.7508
  -1.750   0.1051   0.01711   0.01054  -0.0745   0.8507   0.7922
  -1.500   0.1324   0.01699   0.01044  -0.0733   0.8437   0.8352
  -1.250   0.1626   0.01695   0.01040  -0.0727   0.8369   0.8820
  -1.000   0.2131   0.01690   0.01026  -0.0763   0.8307   0.9287
  -0.750   0.2893   0.01664   0.00980  -0.0852   0.8272   0.9638
  -0.500   0.3682   0.01641   0.00940  -0.0956   0.8215   0.9932
  -0.250   0.3938   0.01636   0.00921  -0.0966   0.8130   1.0000
   0.000   0.4021   0.01668   0.00942  -0.0941   0.8029   1.0000
   0.250   0.4262   0.01675   0.00935  -0.0936   0.7965   1.0000
   0.500   0.4403   0.01721   0.00973  -0.0917   0.7867   1.0000
   0.750   0.4685   0.01729   0.00968  -0.0916   0.7811   1.0000
   1.000   0.4843   0.01781   0.01016  -0.0900   0.7715   1.0000
   1.250   0.5138   0.01790   0.01015  -0.0900   0.7662   1.0000
   1.500   0.5304   0.01849   0.01072  -0.0886   0.7567   1.0000
   1.750   0.5601   0.01859   0.01075  -0.0886   0.7515   1.0000
   2.000   0.5773   0.01922   0.01139  -0.0873   0.7422   1.0000
   2.250   0.6071   0.01934   0.01146  -0.0873   0.7369   1.0000
   2.500   0.6245   0.02000   0.01215  -0.0860   0.7277   1.0000
   2.750   0.6544   0.02012   0.01224  -0.0861   0.7223   1.0000
   3.000   0.6722   0.02081   0.01297  -0.0848   0.7130   1.0000
   3.250   0.7025   0.02089   0.01306  -0.0848   0.7075   1.0000
   3.500   0.7204   0.02158   0.01381  -0.0836   0.6979   1.0000
   3.750   0.7520   0.02157   0.01379  -0.0837   0.6923   1.0000
   4.000   0.7697   0.02225   0.01455  -0.0823   0.6821   1.0000
   4.250   0.8020   0.02217   0.01449  -0.0824   0.6762   1.0000
   4.500   0.8209   0.02274   0.01516  -0.0811   0.6657   1.0000
   4.750   0.8445   0.02307   0.01556  -0.0803   0.6567   1.0000
   5.000   0.8753   0.02292   0.01546  -0.0800   0.6485   1.0000
   5.250   0.8965   0.02326   0.01591  -0.0788   0.6373   1.0000
   5.500   0.9227   0.02329   0.01602  -0.0780   0.6271   1.0000
   5.750   0.9557   0.02288   0.01563  -0.0778   0.6177   1.0000
   6.000   0.9782   0.02298   0.01587  -0.0765   0.6050   1.0000
   6.250   1.0028   0.02291   0.01590  -0.0753   0.5921   1.0000
   6.500   1.0286   0.02269   0.01578  -0.0742   0.5785   1.0000
   6.750   1.0546   0.02238   0.01556  -0.0731   0.5638   1.0000
   7.000   1.0808   0.02199   0.01528  -0.0719   0.5479   1.0000
   7.250   1.1071   0.02151   0.01486  -0.0706   0.5304   1.0000
   7.500   1.1277   0.02124   0.01472  -0.0687   0.5092   1.0000
   7.750   1.1497   0.02083   0.01436  -0.0668   0.4854   1.0000
   8.000   1.1660   0.02069   0.01433  -0.0642   0.4562   1.0000
   8.250   1.1781   0.02079   0.01451  -0.0611   0.4180   1.0000
   8.500   1.1848   0.02118   0.01473  -0.0573   0.3652   1.0000
   8.750   1.1831   0.02225   0.01538  -0.0527   0.3003   1.0000
   9.000   1.1752   0.02385   0.01652  -0.0477   0.2428   1.0000
   9.250   1.1655   0.02561   0.01792  -0.0428   0.1992   1.0000
   9.500   1.1581   0.02752   0.01958  -0.0387   0.1637   1.0000
   9.750   1.1500   0.02971   0.02154  -0.0351   0.1332   1.0000
  10.000   1.1412   0.03221   0.02385  -0.0319   0.1064   1.0000
  10.250   1.1327   0.03499   0.02642  -0.0291   0.0854   1.0000
  10.500   1.1287   0.03772   0.02904  -0.0267   0.0700   1.0000
  10.750   1.1325   0.04012   0.03136  -0.0246   0.0610   1.0000
  11.000   1.1409   0.04224   0.03337  -0.0232   0.0543   1.0000
  11.250   1.1576   0.04412   0.03537  -0.0218   0.0496   1.0000
  11.500   1.1750   0.04605   0.03734  -0.0207   0.0457   1.0000
  11.750   1.2198   0.04904   0.04027  -0.0209   0.0427   1.0000
  12.000   1.2354   0.05176   0.04337  -0.0198   0.0417   1.0000
  12.250   1.2459   0.05495   0.04691  -0.0186   0.0411   1.0000
  12.500   1.2487   0.05837   0.05068  -0.0172   0.0408   1.0000
  12.750   1.2453   0.06188   0.05452  -0.0158   0.0405   1.0000
  13.000   1.2375   0.06560   0.05855  -0.0146   0.0404   1.0000
  13.250   1.2262   0.06960   0.06285  -0.0138   0.0403   1.0000
  13.500   1.2109   0.07392   0.06746  -0.0135   0.0401   1.0000
  13.750   1.1944   0.07871   0.07252  -0.0138   0.0403   1.0000
  14.000   1.1762   0.08389   0.07795  -0.0147   0.0405   1.0000
  14.250   1.1557   0.08959   0.08389  -0.0163   0.0407   1.0000
  14.500   1.1341   0.09581   0.09033  -0.0186   0.0411   1.0000
  14.750   1.1126   0.10247   0.09717  -0.0215   0.0415   1.0000
  15.000   1.0900   0.10978   0.10465  -0.0252   0.0419   1.0000
  15.250   1.0701   0.11742   0.11242  -0.0291   0.0424   1.0000
  15.500   0.9556   0.15174   0.14708  -0.0539   0.0496   1.0000
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