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E387 (e387-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: E387 (e387-il)
Reynolds number: 100,000
Max Cl/Cd: 60.66 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e387-il-100000.txt
Download as CSV file: xf-e387-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E387                                            
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3494   0.10359   0.09882  -0.0293   1.0000   0.0775
  -8.500  -0.3569   0.10207   0.09741  -0.0331   1.0000   0.0784
  -8.250  -0.3669   0.10046   0.09593  -0.0366   1.0000   0.0787
  -8.000  -0.3345   0.09342   0.08882  -0.0310   1.0000   0.0830
  -7.750  -0.3300   0.09063   0.08610  -0.0313   1.0000   0.0860
  -7.500  -0.3321   0.08819   0.08376  -0.0324   1.0000   0.0892
  -7.250  -0.3464   0.08667   0.08240  -0.0355   1.0000   0.0917
  -7.000  -0.3592   0.08488   0.08072  -0.0431   1.0000   0.0926
  -6.750  -0.3585   0.08082   0.07679  -0.0390   1.0000   0.0939
  -6.500  -0.3577   0.07863   0.07469  -0.0333   1.0000   0.0959
  -6.250  -0.3751   0.07784   0.07402  -0.0295   1.0000   0.0967
  -6.000  -0.3934   0.07714   0.07342  -0.0263   1.0000   0.0975
  -5.750  -0.3539   0.07033   0.06637  -0.0462   0.9884   0.1078
  -5.500  -0.3280   0.06660   0.06271  -0.0448   0.9829   0.1121
  -5.250  -0.2881   0.06071   0.05663  -0.0566   0.9728   0.1239
  -5.000  -0.2518   0.05602   0.05174  -0.0647   0.9623   0.1374
  -4.750  -0.2147   0.05183   0.04740  -0.0707   0.9543   0.1520
  -4.500  -0.1794   0.04800   0.04347  -0.0751   0.9461   0.1674
  -4.250  -0.1185   0.03620   0.03002  -0.0860   0.9381   0.0780
  -4.000  -0.0767   0.03078   0.02389  -0.0892   0.9317   0.0639
  -3.750  -0.0393   0.02783   0.02038  -0.0913   0.9237   0.0637
  -3.500   0.0001   0.02508   0.01712  -0.0933   0.9167   0.0631
  -3.250   0.0351   0.02305   0.01466  -0.0942   0.9081   0.0635
  -3.000   0.0731   0.02113   0.01244  -0.0954   0.9013   0.0665
  -2.750   0.1030   0.02003   0.01130  -0.0956   0.8916   0.0766
  -2.500   0.1373   0.01851   0.00989  -0.0962   0.8852   0.1012
  -2.250   0.1612   0.01714   0.00913  -0.0956   0.8747   0.2153
  -2.000   0.1827   0.01539   0.00887  -0.0944   0.8666   0.5432
  -1.750   0.2349   0.01412   0.00834  -0.0967   0.8609   1.0000
  -1.500   0.2622   0.01426   0.00812  -0.0965   0.8520   1.0000
  -1.250   0.2889   0.01441   0.00797  -0.0962   0.8432   1.0000
  -1.000   0.3136   0.01465   0.00798  -0.0957   0.8336   1.0000
  -0.750   0.3417   0.01477   0.00784  -0.0954   0.8267   1.0000
  -0.500   0.3654   0.01508   0.00798  -0.0948   0.8167   1.0000
  -0.250   0.3918   0.01530   0.00802  -0.0944   0.8092   1.0000
   0.000   0.4171   0.01557   0.00814  -0.0940   0.8008   1.0000
   0.250   0.4425   0.01586   0.00830  -0.0935   0.7929   1.0000
   0.500   0.4687   0.01611   0.00842  -0.0931   0.7854   1.0000
   0.750   0.4936   0.01647   0.00870  -0.0927   0.7773   1.0000
   1.000   0.5202   0.01670   0.00883  -0.0923   0.7703   1.0000
   1.250   0.5447   0.01712   0.00920  -0.0920   0.7622   1.0000
   1.500   0.5714   0.01736   0.00936  -0.0916   0.7556   1.0000
   1.750   0.5956   0.01781   0.00980  -0.0912   0.7473   1.0000
   2.000   0.6225   0.01806   0.01000  -0.0908   0.7409   1.0000
   2.250   0.6464   0.01856   0.01051  -0.0904   0.7326   1.0000
   2.500   0.6734   0.01879   0.01071  -0.0900   0.7263   1.0000
   2.750   0.6969   0.01933   0.01128  -0.0896   0.7176   1.0000
   3.000   0.7244   0.01952   0.01148  -0.0892   0.7114   1.0000
   3.250   0.7473   0.02008   0.01210  -0.0887   0.7021   1.0000
   3.500   0.7756   0.02018   0.01218  -0.0882   0.6960   1.0000
   3.750   0.7981   0.02075   0.01284  -0.0876   0.6859   1.0000
   4.000   0.8240   0.02101   0.01318  -0.0870   0.6780   1.0000
   4.250   0.8498   0.02122   0.01344  -0.0863   0.6691   1.0000
   4.500   0.8735   0.02160   0.01391  -0.0856   0.6588   1.0000
   4.750   0.9013   0.02158   0.01393  -0.0848   0.6505   1.0000
   5.000   0.9264   0.02171   0.01419  -0.0839   0.6397   1.0000
   5.250   0.9506   0.02191   0.01450  -0.0830   0.6280   1.0000
   5.500   0.9760   0.02193   0.01462  -0.0820   0.6163   1.0000
   5.750   1.0024   0.02178   0.01457  -0.0809   0.6041   1.0000
   6.000   1.0289   0.02156   0.01447  -0.0798   0.5909   1.0000
   6.250   1.0545   0.02134   0.01436  -0.0786   0.5761   1.0000
   6.500   1.0795   0.02109   0.01424  -0.0773   0.5597   1.0000
   6.750   1.1049   0.02071   0.01400  -0.0760   0.5415   1.0000
   7.000   1.1295   0.02022   0.01361  -0.0744   0.5196   1.0000
   7.250   1.1506   0.01966   0.01316  -0.0722   0.4873   1.0000
   7.500   1.1684   0.01926   0.01274  -0.0697   0.4395   1.0000
   7.750   1.1811   0.01956   0.01285  -0.0669   0.3679   1.0000
   8.000   1.1859   0.02093   0.01362  -0.0636   0.2720   1.0000
   8.250   1.1841   0.02318   0.01523  -0.0601   0.1832   1.0000
   8.500   1.1722   0.02636   0.01761  -0.0557   0.1054   1.0000
   8.750   1.1640   0.02905   0.02002  -0.0513   0.0754   1.0000
   9.000   1.1620   0.03121   0.02211  -0.0478   0.0652   1.0000
   9.250   1.1654   0.03317   0.02403  -0.0452   0.0579   1.0000
   9.500   1.1746   0.03512   0.02603  -0.0431   0.0524   1.0000
   9.750   1.1885   0.03698   0.02789  -0.0415   0.0483   1.0000
  10.000   1.2243   0.04001   0.03083  -0.0418   0.0451   1.0000
  10.250   1.2563   0.04274   0.03386  -0.0419   0.0437   1.0000
  10.500   1.2836   0.04607   0.03754  -0.0418   0.0429   1.0000
  10.750   1.3005   0.04957   0.04143  -0.0407   0.0426   1.0000
  11.000   1.3076   0.05292   0.04517  -0.0388   0.0422   1.0000
  11.250   1.3074   0.05611   0.04873  -0.0364   0.0419   1.0000
  11.500   1.3017   0.05928   0.05223  -0.0338   0.0414   1.0000
  11.750   1.2924   0.06268   0.05595  -0.0315   0.0413   1.0000
  12.000   1.2797   0.06643   0.06000  -0.0298   0.0413   1.0000
  12.250   1.2645   0.07057   0.06443  -0.0287   0.0416   1.0000
  12.500   1.2470   0.07509   0.06922  -0.0284   0.0418   1.0000
  12.750   1.2276   0.08010   0.07448  -0.0289   0.0422   1.0000
  13.000   1.2072   0.08561   0.08021  -0.0301   0.0426   1.0000
  13.250   1.1859   0.09161   0.08642  -0.0322   0.0431   1.0000
  13.500   1.1640   0.09815   0.09313  -0.0350   0.0435   1.0000
  13.750   1.1420   0.10527   0.10041  -0.0386   0.0440   1.0000
  14.000   1.1218   0.11282   0.10808  -0.0426   0.0445   1.0000
  14.250   1.1071   0.12043   0.11575  -0.0461   0.0451   1.0000
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