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MILEY M06-13-128 (miley-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: MILEY M06-13-128 (miley-il)
Reynolds number: 500,000
Max Cl/Cd: 122.83 at α=9.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-miley-il-500000.txt
Download as CSV file: xf-miley-il-500000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.2645   0.08928   0.08572  -0.0189   0.5614   0.0123
  -7.500  -0.2619   0.08606   0.08252  -0.0208   0.5611   0.0123
  -7.250  -0.2625   0.08278   0.07929  -0.0229   0.5609   0.0123
  -7.000  -0.2625   0.07965   0.07618  -0.0254   0.5606   0.0123
  -6.750  -0.2565   0.07585   0.07236  -0.0287   0.5602   0.0124
  -6.500  -0.2480   0.07201   0.06850  -0.0319   0.5599   0.0124
  -6.250  -0.2377   0.06811   0.06455  -0.0346   0.5595   0.0124
  -6.000  -0.2255   0.06409   0.06047  -0.0370   0.5592   0.0124
  -5.750  -0.2185   0.05853   0.05484  -0.0391   0.5589   0.0126
  -5.500  -0.2091   0.05472   0.05098  -0.0401   0.5584   0.0129
  -5.250  -0.1939   0.05165   0.04785  -0.0410   0.5578   0.0131
  -5.000  -0.1769   0.04879   0.04491  -0.0417   0.5574   0.0134
  -4.750  -0.1584   0.04595   0.04196  -0.0423   0.5569   0.0139
  -4.500  -0.1382   0.04305   0.03891  -0.0428   0.5563   0.0144
  -4.250  -0.1169   0.04016   0.03586  -0.0429   0.5558   0.0150
  -4.000  -0.0941   0.03733   0.03283  -0.0427   0.5552   0.0159
  -3.750  -0.0659   0.03547   0.03068  -0.0418   0.5546   0.0175
  -3.500  -0.0409   0.03392   0.02881  -0.0410   0.5537   0.0178
  -3.250  -0.0239   0.02891   0.02341  -0.0402   0.5529   0.0188
  -3.000  -0.0005   0.02728   0.02171  -0.0400   0.5521   0.0196
  -2.750   0.0243   0.02595   0.02023  -0.0396   0.5515   0.0209
  -2.500   0.0504   0.02474   0.01879  -0.0390   0.5508   0.0230
  -2.250   0.0803   0.02565   0.01945  -0.0383   0.5501   0.0256
  -2.000   0.1050   0.02062   0.01395  -0.0365   0.5495   0.0168
  -1.750   0.1320   0.01915   0.01226  -0.0358   0.5488   0.0164
  -1.500   0.1595   0.01859   0.01154  -0.0354   0.5480   0.0184
  -1.250   0.1860   0.01772   0.01058  -0.0349   0.5474   0.0185
  -1.000   0.2121   0.01713   0.00993  -0.0343   0.5467   0.0185
  -0.750   0.2369   0.01659   0.00935  -0.0336   0.5460   0.0200
  -0.500   0.2629   0.01644   0.00920  -0.0333   0.5449   0.0229
  -0.250   0.2894   0.01620   0.00897  -0.0331   0.5435   0.0285
   0.000   0.3164   0.01614   0.00893  -0.0330   0.5419   0.0354
   0.250   0.3383   0.01530   0.00890  -0.0323   0.5403   0.2945
   0.500   0.4415   0.01345   0.00898  -0.0486   0.5389   1.0000
   0.750   0.4669   0.01358   0.00902  -0.0482   0.5376   1.0000
   1.000   0.4925   0.01367   0.00903  -0.0478   0.5364   1.0000
   1.250   0.5183   0.01374   0.00903  -0.0474   0.5355   1.0000
   1.500   0.5443   0.01379   0.00899  -0.0470   0.5345   1.0000
   1.750   0.5703   0.01388   0.00900  -0.0466   0.5336   1.0000
   2.000   0.5962   0.01401   0.00907  -0.0462   0.5327   1.0000
   2.250   0.6216   0.01434   0.00935  -0.0459   0.5313   1.0000
   2.500   0.6472   0.01453   0.00963  -0.0460   0.5279   1.0000
   2.750   0.6734   0.01456   0.00965  -0.0457   0.5254   1.0000
   3.000   0.7001   0.01446   0.00951  -0.0454   0.5235   1.0000
   3.250   0.7274   0.01423   0.00921  -0.0451   0.5220   1.0000
   3.500   0.7549   0.01398   0.00889  -0.0448   0.5205   1.0000
   3.750   0.7822   0.01384   0.00868  -0.0445   0.5192   1.0000
   4.000   0.8090   0.01392   0.00872  -0.0443   0.5182   1.0000
   4.250   0.8345   0.01414   0.00904  -0.0443   0.5153   1.0000
   4.500   0.8607   0.01423   0.00918  -0.0442   0.5126   1.0000
   4.750   0.8877   0.01418   0.00914  -0.0441   0.5107   1.0000
   5.000   0.9149   0.01412   0.00909  -0.0440   0.5091   1.0000
   5.250   0.9423   0.01402   0.00899  -0.0439   0.5078   1.0000
   5.500   0.9699   0.01389   0.00886  -0.0438   0.5066   1.0000
   5.750   0.9978   0.01373   0.00867  -0.0437   0.5054   1.0000
   6.000   1.0257   0.01361   0.00854  -0.0437   0.5042   1.0000
   6.250   1.0509   0.01376   0.00885  -0.0437   0.5001   1.0000
   6.500   1.0779   0.01368   0.00883  -0.0436   0.4973   1.0000
   6.750   1.1058   0.01346   0.00865  -0.0436   0.4952   1.0000
   7.000   1.1342   0.01315   0.00836  -0.0436   0.4934   1.0000
   7.250   1.1629   0.01281   0.00802  -0.0437   0.4917   1.0000
   7.500   1.1892   0.01280   0.00814  -0.0437   0.4879   1.0000
   7.750   1.2164   0.01268   0.00813  -0.0437   0.4838   1.0000
   8.000   1.2447   0.01235   0.00786  -0.0438   0.4806   1.0000
   8.250   1.2732   0.01201   0.00756  -0.0438   0.4774   1.0000
   8.500   1.2998   0.01199   0.00771  -0.0439   0.4698   1.0000
   8.750   1.3280   0.01172   0.00753  -0.0440   0.4632   1.0000
   9.000   1.3559   0.01146   0.00734  -0.0441   0.4504   1.0000
   9.250   1.3818   0.01125   0.00698  -0.0439   0.4170   1.0000
   9.500   1.3953   0.01251   0.00783  -0.0429   0.3567   1.0000
   9.750   1.4052   0.01430   0.00936  -0.0419   0.3072   1.0000
  10.000   1.4134   0.01618   0.01110  -0.0412   0.2727   1.0000
  10.250   1.4210   0.01813   0.01299  -0.0409   0.2487   1.0000
  10.500   1.4211   0.02199   0.01687  -0.0432   0.2288   1.0000
  10.750   1.4053   0.02565   0.02051  -0.0423   0.2179   1.0000
  11.000   1.3916   0.02895   0.02375  -0.0413   0.2023   1.0000
  11.250   1.3843   0.03171   0.02647  -0.0404   0.1888   1.0000
  11.500   1.3669   0.03531   0.02991  -0.0392   0.1621   1.0000
  11.750   1.3489   0.03895   0.03335  -0.0381   0.1316   1.0000
  12.000   1.3217   0.04349   0.03755  -0.0368   0.0890   1.0000
  12.250   1.3080   0.04713   0.04101  -0.0360   0.0610   1.0000
  12.500   1.2953   0.05083   0.04451  -0.0354   0.0345   1.0000
  12.750   1.2762   0.05542   0.04892  -0.0348   0.0114   1.0000
  13.000   1.2725   0.05855   0.05208  -0.0344   0.0076   1.0000
  13.250   1.2720   0.06142   0.05502  -0.0343   0.0062   1.0000
  13.500   1.2663   0.06495   0.05866  -0.0341   0.0054   1.0000
  13.750   1.2682   0.06766   0.06145  -0.0341   0.0052   1.0000
  14.000   1.2681   0.07066   0.06456  -0.0342   0.0050   1.0000
  14.250   1.2663   0.07394   0.06793  -0.0343   0.0045   1.0000
  14.500   1.2632   0.07743   0.07151  -0.0345   0.0042   1.0000
  14.750   1.2604   0.08094   0.07511  -0.0348   0.0039   1.0000
  15.000   1.2571   0.08460   0.07887  -0.0352   0.0039   1.0000
  15.250   1.2538   0.08826   0.08263  -0.0357   0.0039   1.0000
  15.500   1.2498   0.09210   0.08656  -0.0362   0.0039   1.0000
  15.750   1.2313   0.09797   0.09253  -0.0370   0.0035   1.0000
  16.000   1.2277   0.10181   0.09644  -0.0376   0.0035   1.0000
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