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MILEY M06-13-128 (miley-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: MILEY M06-13-128 (miley-il)
Reynolds number: 500,000
Max Cl/Cd: 121.43 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-miley-il-500000-n5.txt
Download as CSV file: xf-miley-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MILEY M06-13-128                                
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.2112   0.08670   0.08297  -0.0110   0.5309   0.0075
  -8.000  -0.2082   0.08293   0.07920  -0.0124   0.5306   0.0075
  -7.750  -0.2053   0.07925   0.07554  -0.0139   0.5304   0.0075
  -7.500  -0.2038   0.07533   0.07164  -0.0154   0.5303   0.0075
  -7.250  -0.2025   0.07160   0.06793  -0.0170   0.5301   0.0075
  -7.000  -0.2022   0.06786   0.06423  -0.0186   0.5299   0.0075
  -6.750  -0.2043   0.06412   0.06052  -0.0204   0.5296   0.0075
  -6.500  -0.2099   0.06053   0.05696  -0.0224   0.5293   0.0075
  -6.250  -0.2077   0.05619   0.05261  -0.0257   0.5289   0.0075
  -6.000  -0.2024   0.05168   0.04807  -0.0287   0.5286   0.0075
  -5.750  -0.1945   0.04699   0.04333  -0.0314   0.5282   0.0075
  -5.250  -0.1716   0.03776   0.03393  -0.0354   0.5275   0.0075
  -4.750  -0.1526   0.04190   0.03739  -0.0413   0.5272   0.0045
  -4.500  -0.1326   0.03832   0.03361  -0.0415   0.5268   0.0044
  -4.250  -0.1115   0.03468   0.02973  -0.0413   0.5264   0.0043
  -4.000  -0.0896   0.03105   0.02582  -0.0407   0.5260   0.0042
  -3.750  -0.0670   0.02736   0.02177  -0.0396   0.5256   0.0042
  -3.500  -0.0437   0.02355   0.01751  -0.0381   0.5252   0.0043
  -3.250  -0.0194   0.01979   0.01319  -0.0363   0.5248   0.0047
  -3.000   0.0060   0.01807   0.01116  -0.0356   0.5244   0.0051
  -2.750   0.0329   0.01743   0.01038  -0.0354   0.5238   0.0054
  -2.500   0.0602   0.01700   0.00985  -0.0352   0.5232   0.0060
  -2.250   0.0876   0.01632   0.00900  -0.0349   0.5226   0.0069
  -2.000   0.1146   0.01543   0.00795  -0.0344   0.5221   0.0071
  -1.750   0.1413   0.01469   0.00710  -0.0339   0.5216   0.0072
  -1.500   0.1679   0.01413   0.00645  -0.0335   0.5211   0.0074
  -1.250   0.1942   0.01359   0.00585  -0.0331   0.5207   0.0078
  -1.000   0.2212   0.01330   0.00554  -0.0329   0.5202   0.0087
  -0.750   0.2486   0.01306   0.00526  -0.0327   0.5197   0.0108
  -0.500   0.2760   0.01284   0.00499  -0.0325   0.5192   0.0139
  -0.250   0.3036   0.01272   0.00485  -0.0325   0.5186   0.0195
   0.000   0.3314   0.01264   0.00473  -0.0324   0.5182   0.0228
   0.250   0.3591   0.01259   0.00464  -0.0324   0.5176   0.0286
   0.500   0.3855   0.01231   0.00462  -0.0322   0.5171   0.1237
   0.750   0.4075   0.01147   0.00465  -0.0316   0.5164   0.4248
   1.250   0.5303   0.01007   0.00478  -0.0462   0.5144   1.0000
   1.500   0.5567   0.01016   0.00484  -0.0460   0.5132   1.0000
   1.750   0.5832   0.01023   0.00488  -0.0457   0.5120   1.0000
   2.000   0.6097   0.01030   0.00492  -0.0456   0.5108   1.0000
   2.250   0.6364   0.01035   0.00494  -0.0454   0.5096   1.0000
   2.500   0.6632   0.01037   0.00493  -0.0452   0.5084   1.0000
   2.750   0.6902   0.01035   0.00487  -0.0450   0.5071   1.0000
   3.000   0.7173   0.01028   0.00475  -0.0449   0.5057   1.0000
   3.250   0.7447   0.01017   0.00456  -0.0447   0.5041   1.0000
   3.500   0.7715   0.01016   0.00461  -0.0446   0.5012   1.0000
   3.750   0.7985   0.01016   0.00464  -0.0445   0.4986   1.0000
   4.000   0.8255   0.01019   0.00468  -0.0445   0.4969   1.0000
   4.250   0.8526   0.01020   0.00470  -0.0444   0.4954   1.0000
   4.500   0.8799   0.01019   0.00470  -0.0444   0.4939   1.0000
   4.750   0.9072   0.01015   0.00466  -0.0444   0.4925   1.0000
   5.000   0.9345   0.01014   0.00465  -0.0443   0.4913   1.0000
   5.250   0.9613   0.01025   0.00484  -0.0444   0.4890   1.0000
   5.500   0.9882   0.01035   0.00503  -0.0444   0.4861   1.0000
   5.750   1.0154   0.01036   0.00509  -0.0444   0.4832   1.0000
   6.000   1.0429   0.01031   0.00508  -0.0445   0.4806   1.0000
   6.250   1.0704   0.01025   0.00506  -0.0445   0.4784   1.0000
   6.500   1.0970   0.01043   0.00535  -0.0446   0.4737   1.0000
   6.750   1.1243   0.01043   0.00541  -0.0447   0.4694   1.0000
   7.000   1.1517   0.01038   0.00540  -0.0447   0.4648   1.0000
   7.250   1.1789   0.01039   0.00550  -0.0448   0.4573   1.0000
   7.500   1.2062   0.01034   0.00548  -0.0449   0.4492   1.0000
   7.750   1.2332   0.01030   0.00544  -0.0449   0.4381   1.0000
   8.000   1.2592   0.01037   0.00548  -0.0449   0.4216   1.0000
   8.250   1.2833   0.01068   0.00571  -0.0447   0.4014   1.0000
   8.500   1.3063   0.01117   0.00616  -0.0444   0.3816   1.0000
   8.750   1.3275   0.01185   0.00678  -0.0441   0.3599   1.0000
   9.000   1.3476   0.01265   0.00753  -0.0437   0.3368   1.0000
   9.250   1.3669   0.01349   0.00835  -0.0434   0.3182   1.0000
   9.500   1.3843   0.01451   0.00933  -0.0429   0.2968   1.0000
   9.750   1.3896   0.01669   0.01132  -0.0422   0.2566   1.0000
  10.000   1.3867   0.02053   0.01504  -0.0435   0.2219   1.0000
  10.250   1.3721   0.02474   0.01922  -0.0439   0.2067   1.0000
  10.500   1.3576   0.02803   0.02245  -0.0426   0.1917   1.0000
  10.750   1.3426   0.03139   0.02569  -0.0415   0.1692   1.0000
  11.000   1.3304   0.03452   0.02869  -0.0404   0.1464   1.0000
  11.250   1.3176   0.03769   0.03169  -0.0393   0.1204   1.0000
  11.500   1.3042   0.04095   0.03479  -0.0382   0.0942   1.0000
  11.750   1.2914   0.04434   0.03799  -0.0373   0.0678   1.0000
  12.000   1.2830   0.04755   0.04105  -0.0367   0.0441   1.0000
  12.250   1.2767   0.05064   0.04403  -0.0361   0.0252   1.0000
  12.500   1.2765   0.05326   0.04663  -0.0358   0.0165   1.0000
  12.750   1.2741   0.05615   0.04948  -0.0355   0.0080   1.0000
  13.000   1.2722   0.05908   0.05242  -0.0353   0.0037   1.0000
  13.250   1.2742   0.06164   0.05503  -0.0352   0.0025   1.0000
  13.500   1.2781   0.06401   0.05747  -0.0351   0.0018   1.0000
  13.750   1.2820   0.06643   0.05996  -0.0351   0.0017   1.0000
  14.000   1.2848   0.06902   0.06265  -0.0351   0.0016   1.0000
  14.250   1.2845   0.07204   0.06576  -0.0351   0.0012   1.0000
  14.500   1.2860   0.07484   0.06865  -0.0353   0.0009   1.0000
  14.750   1.2869   0.07780   0.07171  -0.0354   0.0010   1.0000
  15.000   1.2875   0.08083   0.07482  -0.0357   0.0009   1.0000
  15.250   1.2852   0.08428   0.07837  -0.0361   0.0007   1.0000
  15.500   1.2850   0.08747   0.08165  -0.0364   0.0007   1.0000
  15.750   1.2843   0.09081   0.08509  -0.0369   0.0008   1.0000
  16.000   1.2763   0.09525   0.08964  -0.0376   0.0005   1.0000
  16.250   1.2743   0.09885   0.09333  -0.0383   0.0006   1.0000
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