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E387 (e387-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: E387 (e387-il)
Reynolds number: 500,000
Max Cl/Cd: 109.14 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e387-il-500000-n5.txt
Download as CSV file: xf-e387-il-500000-n5.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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3475   0.09135   0.08914  -0.0306   1.0000   0.0110
  -8.500  -0.3438   0.08824   0.08605  -0.0317   1.0000   0.0110
  -8.250  -0.3418   0.08462   0.08247  -0.0333   1.0000   0.0111
  -7.750  -0.3061   0.07144   0.06917  -0.0496   0.9104   0.0074
  -7.500  -0.3043   0.06787   0.06544  -0.0524   0.8627   0.0072
  -7.250  -0.3037   0.06277   0.06022  -0.0570   0.8321   0.0073
  -7.000  -0.2972   0.05835   0.05568  -0.0615   0.8101   0.0071
  -6.750  -0.2887   0.05188   0.04907  -0.0677   0.7925   0.0072
  -6.500  -0.2765   0.04518   0.04216  -0.0730   0.7781   0.0070
  -6.250  -0.2631   0.03675   0.03338  -0.0775   0.7661   0.0070
  -6.000  -0.2499   0.02691   0.02287  -0.0800   0.7558   0.0070
  -5.750  -0.2292   0.02243   0.01774  -0.0805   0.7456   0.0074
  -5.500  -0.2047   0.02055   0.01540  -0.0804   0.7356   0.0076
  -5.250  -0.1803   0.01850   0.01293  -0.0803   0.7259   0.0077
  -5.000  -0.1549   0.01694   0.01103  -0.0802   0.7170   0.0077
  -4.500  -0.1031   0.01408   0.00756  -0.0798   0.7005   0.0078
  -4.250  -0.0769   0.01302   0.00629  -0.0796   0.6927   0.0080
  -4.000  -0.0501   0.01223   0.00538  -0.0794   0.6851   0.0082
  -3.750  -0.0232   0.01166   0.00469  -0.0793   0.6782   0.0086
  -3.500   0.0041   0.01118   0.00413  -0.0792   0.6711   0.0090
  -3.250   0.0314   0.01080   0.00364  -0.0790   0.6646   0.0096
  -3.000   0.0591   0.01045   0.00321  -0.0790   0.6581   0.0102
  -2.750   0.0867   0.01021   0.00288  -0.0789   0.6519   0.0109
  -2.500   0.1144   0.00990   0.00249  -0.0788   0.6459   0.0123
  -2.250   0.1423   0.00968   0.00221  -0.0788   0.6398   0.0134
  -2.000   0.1702   0.00952   0.00196  -0.0787   0.6344   0.0153
  -1.750   0.1981   0.00927   0.00177  -0.0787   0.6285   0.0306
  -1.500   0.2257   0.00902   0.00163  -0.0787   0.6230   0.0728
  -1.250   0.2533   0.00877   0.00154  -0.0788   0.6179   0.1265
  -1.000   0.2810   0.00853   0.00148  -0.0789   0.6123   0.1894
  -0.750   0.3083   0.00829   0.00143  -0.0790   0.6071   0.2716
  -0.500   0.3357   0.00798   0.00141  -0.0791   0.6020   0.3740
  -0.250   0.3625   0.00763   0.00142  -0.0791   0.5967   0.5045
   0.000   0.3886   0.00733   0.00144  -0.0788   0.5918   0.6255
   0.250   0.4140   0.00702   0.00147  -0.0782   0.5867   0.7397
   0.500   0.4351   0.00668   0.00151  -0.0764   0.5817   0.8761
   0.750   0.4753   0.00659   0.00146  -0.0788   0.5766   1.0000
   1.000   0.5031   0.00665   0.00148  -0.0788   0.5713   1.0000
   1.250   0.5308   0.00672   0.00150  -0.0787   0.5661   1.0000
   1.500   0.5584   0.00680   0.00153  -0.0787   0.5611   1.0000
   1.750   0.5862   0.00687   0.00158  -0.0786   0.5555   1.0000
   2.000   0.6138   0.00696   0.00162  -0.0786   0.5498   1.0000
   2.250   0.6415   0.00704   0.00168  -0.0785   0.5433   1.0000
   2.500   0.6689   0.00714   0.00174  -0.0785   0.5360   1.0000
   2.750   0.6965   0.00722   0.00182  -0.0784   0.5283   1.0000
   3.000   0.7237   0.00734   0.00189  -0.0783   0.5197   1.0000
   3.250   0.7512   0.00743   0.00198  -0.0783   0.5104   1.0000
   3.500   0.7785   0.00754   0.00209  -0.0782   0.5015   1.0000
   4.000   0.8327   0.00780   0.00231  -0.0780   0.4799   1.0000
   4.250   0.8596   0.00794   0.00244  -0.0779   0.4673   1.0000
   4.500   0.8862   0.00812   0.00260  -0.0777   0.4512   1.0000
   4.750   0.9120   0.00836   0.00276  -0.0774   0.4256   1.0000
   5.000   0.9365   0.00875   0.00298  -0.0770   0.3856   1.0000
   5.250   0.9579   0.00949   0.00336  -0.0762   0.3130   1.0000
   5.500   0.9777   0.01046   0.00393  -0.0753   0.2343   1.0000
   5.750   0.9993   0.01121   0.00443  -0.0746   0.1834   1.0000
   6.250   1.0416   0.01273   0.00549  -0.0731   0.0944   1.0000
   6.500   1.0620   0.01354   0.00610  -0.0722   0.0571   1.0000
   6.750   1.0824   0.01431   0.00672  -0.0713   0.0302   1.0000
   7.000   1.1023   0.01511   0.00741  -0.0703   0.0126   1.0000
   7.250   1.1246   0.01563   0.00796  -0.0696   0.0106   1.0000
   7.500   1.1469   0.01613   0.00853  -0.0689   0.0098   1.0000
   7.750   1.1686   0.01665   0.00912  -0.0681   0.0093   1.0000
   8.000   1.1896   0.01722   0.00977  -0.0672   0.0089   1.0000
   8.250   1.2096   0.01786   0.01048  -0.0662   0.0084   1.0000
   8.500   1.2284   0.01855   0.01124  -0.0650   0.0080   1.0000
   8.750   1.2454   0.01936   0.01212  -0.0636   0.0076   1.0000
   9.000   1.2593   0.02035   0.01322  -0.0619   0.0072   1.0000
   9.250   1.2715   0.02138   0.01434  -0.0599   0.0070   1.0000
   9.500   1.2826   0.02226   0.01531  -0.0576   0.0069   1.0000
   9.750   1.2922   0.02316   0.01629  -0.0553   0.0068   1.0000
  10.000   1.2997   0.02424   0.01746  -0.0529   0.0067   1.0000
  10.250   1.3069   0.02542   0.01872  -0.0507   0.0066   1.0000
  10.500   1.3131   0.02675   0.02015  -0.0486   0.0065   1.0000
  10.750   1.3190   0.02822   0.02173  -0.0468   0.0064   1.0000
  11.000   1.3246   0.02981   0.02343  -0.0453   0.0063   1.0000
  11.250   1.3294   0.03158   0.02530  -0.0438   0.0062   1.0000
  11.500   1.3346   0.03341   0.02724  -0.0426   0.0060   1.0000
  11.750   1.3385   0.03546   0.02940  -0.0415   0.0060   1.0000
  12.000   1.3427   0.03755   0.03161  -0.0406   0.0059   1.0000
  12.250   1.3464   0.03978   0.03395  -0.0397   0.0058   1.0000
  12.500   1.3500   0.04207   0.03636  -0.0391   0.0056   1.0000
  12.750   1.3524   0.04458   0.03900  -0.0385   0.0056   1.0000
  13.000   1.3545   0.04719   0.04175  -0.0380   0.0055   1.0000
  13.250   1.3562   0.04988   0.04456  -0.0378   0.0054   1.0000
  13.500   1.3571   0.05274   0.04755  -0.0377   0.0054   1.0000
  13.750   1.3571   0.05577   0.05072  -0.0378   0.0052   1.0000
  14.000   1.3563   0.05895   0.05401  -0.0381   0.0051   1.0000
  14.250   1.3541   0.06247   0.05767  -0.0385   0.0051   1.0000
  14.500   1.3507   0.06625   0.06159  -0.0392   0.0050   1.0000
  14.750   1.3472   0.07015   0.06561  -0.0402   0.0049   1.0000
  15.000   1.3425   0.07441   0.07001  -0.0413   0.0049   1.0000
  15.250   1.3362   0.07909   0.07484  -0.0428   0.0048   1.0000
  15.500   1.3281   0.08421   0.08011  -0.0446   0.0048   1.0000
  15.750   1.3200   0.08957   0.08562  -0.0468   0.0048   1.0000
  16.000   1.3099   0.09546   0.09167  -0.0493   0.0047   1.0000
  16.250   1.2995   0.10166   0.09804  -0.0522   0.0047   1.0000
  16.500   1.2872   0.10844   0.10498  -0.0556   0.0047   1.0000
  16.750   1.2752   0.11545   0.11215  -0.0593   0.0047   1.0000
  17.000   1.2628   0.12285   0.11971  -0.0635   0.0047   1.0000
  17.250   1.2496   0.13069   0.12772  -0.0681   0.0047   1.0000
  17.500   1.2368   0.13875   0.13593  -0.0730   0.0047   1.0000
  17.750   1.2234   0.14730   0.14463  -0.0783   0.0047   1.0000
  18.000   1.2097   0.15635   0.15383  -0.0840   0.0047   1.0000
  18.250   1.1947   0.16619   0.16382  -0.0902   0.0047   1.0000
  18.500   1.1753   0.17810   0.17590  -0.0977   0.0048   1.0000
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