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MILEY M06-13-128 (miley-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: MILEY M06-13-128 (miley-il)
Reynolds number: 100,000
Max Cl/Cd: 23.16 at α=12.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-miley-il-100000-n5.txt
Download as CSV file: xf-miley-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2863   0.11777   0.11215  -0.0127   0.6032   0.0328
  -9.000  -0.2829   0.11501   0.10943  -0.0154   0.6028   0.0330
  -8.750  -0.2801   0.11215   0.10661  -0.0182   0.6023   0.0332
  -8.500  -0.2757   0.10913   0.10362  -0.0206   0.6017   0.0332
  -8.250  -0.2737   0.10596   0.10048  -0.0235   0.6012   0.0333
  -8.000  -0.2562   0.10021   0.09471  -0.0199   0.6005   0.0349
  -7.750  -0.2474   0.09714   0.09168  -0.0208   0.5998   0.0358
  -7.500  -0.2396   0.09425   0.08884  -0.0219   0.5991   0.0380
  -7.250  -0.2349   0.09127   0.08592  -0.0239   0.5985   0.0393
  -7.000  -0.2338   0.08851   0.08321  -0.0266   0.5979   0.0416
  -6.750  -0.2339   0.08570   0.08045  -0.0305   0.5973   0.0429
  -6.500  -0.2296   0.08271   0.07742  -0.0389   0.5967   0.0445
  -6.250  -0.2208   0.07972   0.07426  -0.0433   0.5960   0.0448
  -6.000  -0.2125   0.07456   0.06927  -0.0420   0.5952   0.0465
  -5.750  -0.2005   0.07201   0.06676  -0.0412   0.5942   0.0493
  -5.500  -0.1875   0.06892   0.06361  -0.0433   0.5931   0.0524
  -5.250  -0.1685   0.06700   0.06111  -0.0492   0.5921   0.0582
  -5.000  -0.1563   0.06177   0.05597  -0.0499   0.5912   0.0596
  -4.750  -0.1406   0.05864   0.05288  -0.0501   0.5905   0.0613
  -4.250  -0.0932   0.05022   0.04369  -0.0512   0.5890   0.0321
  -4.000  -0.0749   0.04703   0.04034  -0.0513   0.5883   0.0289
  -3.750  -0.0483   0.04364   0.03623  -0.0503   0.5875   0.0235
  -3.500  -0.0275   0.04100   0.03333  -0.0499   0.5867   0.0227
  -3.250  -0.0038   0.03891   0.03094  -0.0500   0.5851   0.0221
  -3.000   0.0209   0.03706   0.02876  -0.0500   0.5836   0.0217
  -2.750   0.0462   0.03550   0.02686  -0.0498   0.5823   0.0214
  -2.500   0.0722   0.03412   0.02513  -0.0495   0.5807   0.0214
  -2.250   0.0985   0.03289   0.02359  -0.0491   0.5790   0.0215
  -2.000   0.1252   0.03204   0.02244  -0.0486   0.5775   0.0231
  -1.750   0.1509   0.03104   0.02129  -0.0483   0.5762   0.0255
  -1.500   0.1765   0.03035   0.02049  -0.0480   0.5751   0.0277
  -1.250   0.2015   0.02967   0.01972  -0.0472   0.5740   0.0298
  -1.000   0.2257   0.02913   0.01907  -0.0464   0.5730   0.0351
  -0.750   0.2490   0.02924   0.01919  -0.0466   0.5701   0.0403
  -0.500   0.2726   0.02943   0.01933  -0.0468   0.5674   0.0491
  -0.250   0.3643   0.02626   0.01898  -0.0594   0.5655   1.0000
   0.000   0.3875   0.02673   0.01917  -0.0590   0.5634   1.0000
   0.250   0.4107   0.02716   0.01936  -0.0584   0.5618   1.0000
   0.500   0.4340   0.02751   0.01948  -0.0577   0.5603   1.0000
   0.750   0.4576   0.02781   0.01958  -0.0569   0.5591   1.0000
   1.000   0.4772   0.02920   0.02094  -0.0578   0.5541   1.0000
   1.250   0.4985   0.02998   0.02161  -0.0577   0.5507   1.0000
   1.500   0.5211   0.03046   0.02196  -0.0572   0.5485   1.0000
   1.750   0.5445   0.03080   0.02217  -0.0565   0.5467   1.0000
   2.000   0.5683   0.03107   0.02231  -0.0557   0.5454   1.0000
   2.500   0.6039   0.03346   0.02467  -0.0560   0.5352   1.0000
   2.750   0.6275   0.03373   0.02486  -0.0553   0.5332   1.0000
   3.000   0.6521   0.03389   0.02493  -0.0544   0.5316   1.0000
   3.500   0.6843   0.03625   0.02730  -0.0543   0.5204   1.0000
   3.750   0.7094   0.03629   0.02729  -0.0535   0.5186   1.0000
   4.000   0.7357   0.03620   0.02717  -0.0526   0.5173   1.0000
   4.500   0.7662   0.03835   0.02936  -0.0522   0.5051   1.0000
   4.750   0.7931   0.03816   0.02914  -0.0513   0.5036   1.0000
   5.250   0.8201   0.04030   0.03137  -0.0507   0.4902   1.0000
   5.500   0.8232   0.04211   0.03323  -0.0505   0.4805   1.0000
   5.750   0.8490   0.04194   0.03307  -0.0498   0.4781   1.0000
   6.000   0.8465   0.04384   0.03499  -0.0489   0.4679   1.0000
   6.500   0.8684   0.04544   0.03663  -0.0467   0.4553   1.0000
   7.000   0.8929   0.04708   0.03837  -0.0450   0.4427   1.0000
   7.250   0.9196   0.04674   0.03809  -0.0444   0.4404   1.0000
   7.500   0.9202   0.04856   0.03996  -0.0435   0.4300   1.0000
   7.750   0.9403   0.04877   0.04023  -0.0428   0.4257   1.0000
   8.000   0.9490   0.05000   0.04155  -0.0421   0.4175   1.0000
   8.250   0.9755   0.04959   0.04122  -0.0415   0.4151   1.0000
   8.500   0.9795   0.05132   0.04301  -0.0408   0.4053   1.0000
   8.750   1.0050   0.05091   0.04269  -0.0402   0.4023   1.0000
   9.250   1.0354   0.05222   0.04421  -0.0389   0.3897   1.0000
   9.500   1.0638   0.05150   0.04361  -0.0382   0.3874   1.0000
   9.750   1.0681   0.05333   0.04552  -0.0376   0.3775   1.0000
  10.000   1.0964   0.05258   0.04489  -0.0370   0.3745   1.0000
  10.500   1.1300   0.05363   0.04619  -0.0357   0.3618   1.0000
  10.750   1.1619   0.05247   0.04517  -0.0349   0.3588   1.0000
  11.000   1.1657   0.05444   0.04725  -0.0344   0.3490   1.0000
  11.250   1.1985   0.05319   0.04615  -0.0336   0.3460   1.0000
  11.500   1.2015   0.05528   0.04836  -0.0330   0.3365   1.0000
  11.750   1.2343   0.05401   0.04728  -0.0322   0.3324   1.0000
  12.000   1.2382   0.05600   0.04939  -0.0316   0.3232   1.0000
  12.250   1.2691   0.05480   0.04832  -0.0307   0.3162   1.0000
  12.500   1.2757   0.05637   0.05000  -0.0301   0.3060   1.0000
  12.750   1.2818   0.05803   0.05179  -0.0295   0.2962   1.0000
  13.000   1.2883   0.05948   0.05331  -0.0289   0.2830   1.0000
  13.250   1.2905   0.06117   0.05488  -0.0283   0.2617   1.0000
  13.500   1.2786   0.06514   0.05885  -0.0285   0.2430   1.0000
  13.750   1.2710   0.06863   0.06226  -0.0287   0.2225   1.0000
  14.000   1.2612   0.07269   0.06630  -0.0291   0.2021   1.0000
  14.250   1.2492   0.07721   0.07074  -0.0298   0.1768   1.0000
  14.500   1.2388   0.08167   0.07516  -0.0305   0.1492   1.0000
  14.750   1.2233   0.08689   0.08014  -0.0314   0.1165   1.0000
  15.000   1.2051   0.09274   0.08576  -0.0327   0.0899   1.0000
  15.250   1.1870   0.09881   0.09167  -0.0341   0.0690   1.0000
  15.500   1.1726   0.10455   0.09735  -0.0356   0.0520   1.0000
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