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M6 (85%) (m685-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: M6 (85%) (m685-il)
Reynolds number: 200,000
Max Cl/Cd: 66.92 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-m685-il-200000.txt
Download as CSV file: xf-m685-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: M6 (85%)                                        
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4894   0.08961   0.08600  -0.0266   1.0000   0.0565
  -9.000  -0.5141   0.08325   0.07967  -0.0352   1.0000   0.0573
  -8.750  -0.5422   0.07936   0.07572  -0.0356   1.0000   0.0576
  -8.500  -0.5652   0.07593   0.07213  -0.0345   1.0000   0.0578
  -8.250  -0.5563   0.07038   0.06673  -0.0339   1.0000   0.0588
  -8.000  -0.5441   0.06837   0.06480  -0.0320   1.0000   0.0601
  -7.750  -0.5425   0.06580   0.06221  -0.0305   1.0000   0.0614
  -7.500  -0.5441   0.06285   0.05922  -0.0291   1.0000   0.0629
  -7.250  -0.5477   0.05962   0.05587  -0.0273   1.0000   0.0657
  -7.000  -0.5757   0.05543   0.05111  -0.0226   1.0000   0.0697
  -6.750  -0.5648   0.05180   0.04764  -0.0213   1.0000   0.0710
  -6.500  -0.5564   0.04975   0.04565  -0.0191   1.0000   0.0729
  -6.250  -0.5530   0.04770   0.04354  -0.0160   1.0000   0.0751
  -6.000  -0.5646   0.04912   0.04429  -0.0086   1.0000   0.0822
  -5.750  -0.5735   0.04328   0.03856  -0.0052   1.0000   0.0840
  -5.500  -0.5602   0.03044   0.02403  -0.0011   0.9924   0.0481
  -5.250  -0.5255   0.02722   0.02040  -0.0031   0.9860   0.0478
  -5.000  -0.4903   0.02498   0.01775  -0.0047   0.9781   0.0484
  -4.750  -0.4532   0.02237   0.01485  -0.0068   0.9719   0.0491
  -4.500  -0.4138   0.02054   0.01279  -0.0090   0.9651   0.0494
  -4.250  -0.3732   0.01896   0.01110  -0.0115   0.9587   0.0503
  -4.000  -0.3316   0.01770   0.00976  -0.0142   0.9518   0.0519
  -3.750  -0.2896   0.01661   0.00862  -0.0169   0.9449   0.0547
  -3.500  -0.2497   0.01563   0.00757  -0.0191   0.9356   0.0583
  -3.250  -0.2139   0.01468   0.00670  -0.0208   0.9241   0.0644
  -3.000  -0.1784   0.01395   0.00598  -0.0222   0.9122   0.0739
  -2.750  -0.1461   0.01333   0.00539  -0.0230   0.8989   0.0867
  -2.500  -0.1189   0.01275   0.00488  -0.0226   0.8837   0.1122
  -2.250  -0.0988   0.01184   0.00444  -0.0210   0.8683   0.2071
  -2.000  -0.0869   0.01076   0.00414  -0.0179   0.8528   0.4007
  -1.750   0.0082   0.00998   0.00504  -0.0298   0.8464   0.9074
  -1.500   0.0900   0.01115   0.00597  -0.0388   0.8367   0.9448
  -1.250   0.1618   0.01162   0.00625  -0.0469   0.8232   0.9678
  -1.000   0.2369   0.01157   0.00601  -0.0563   0.8091   0.9875
  -0.750   0.2978   0.01114   0.00542  -0.0633   0.7940   1.0000
  -0.500   0.3187   0.01113   0.00529  -0.0621   0.7788   1.0000
  -0.250   0.3398   0.01113   0.00518  -0.0608   0.7648   1.0000
   0.000   0.3612   0.01114   0.00509  -0.0596   0.7517   1.0000
   0.250   0.3827   0.01116   0.00501  -0.0585   0.7394   1.0000
   0.500   0.4044   0.01117   0.00496  -0.0573   0.7269   1.0000
   0.750   0.4260   0.01120   0.00493  -0.0562   0.7145   1.0000
   1.000   0.4480   0.01124   0.00490  -0.0551   0.7032   1.0000
   1.250   0.4702   0.01129   0.00488  -0.0540   0.6924   1.0000
   1.500   0.4920   0.01133   0.00489  -0.0528   0.6800   1.0000
   1.750   0.5141   0.01138   0.00491  -0.0517   0.6681   1.0000
   2.000   0.5361   0.01143   0.00491  -0.0505   0.6560   1.0000
   2.250   0.5581   0.01149   0.00491  -0.0493   0.6437   1.0000
   2.500   0.5801   0.01153   0.00495  -0.0481   0.6307   1.0000
   2.750   0.6020   0.01159   0.00500  -0.0469   0.6179   1.0000
   3.000   0.6243   0.01166   0.00507  -0.0458   0.6062   1.0000
   3.250   0.6468   0.01175   0.00513  -0.0447   0.5951   1.0000
   3.500   0.6689   0.01182   0.00521  -0.0435   0.5824   1.0000
   3.750   0.6907   0.01189   0.00530  -0.0423   0.5684   1.0000
   4.000   0.7124   0.01196   0.00537  -0.0410   0.5538   1.0000
   4.250   0.7339   0.01203   0.00545  -0.0397   0.5384   1.0000
   4.500   0.7553   0.01212   0.00555  -0.0383   0.5224   1.0000
   4.750   0.7765   0.01221   0.00563  -0.0369   0.5051   1.0000
   5.000   0.7968   0.01229   0.00569  -0.0354   0.4826   1.0000
   5.250   0.8167   0.01241   0.00579  -0.0338   0.4581   1.0000
   5.500   0.8367   0.01257   0.00594  -0.0322   0.4334   1.0000
   5.750   0.8559   0.01279   0.00611  -0.0305   0.4046   1.0000
   6.000   0.8744   0.01308   0.00632  -0.0288   0.3703   1.0000
   6.250   0.8910   0.01350   0.00659  -0.0268   0.3247   1.0000
   6.500   0.9052   0.01416   0.00697  -0.0245   0.2646   1.0000
   6.750   0.9148   0.01524   0.00760  -0.0216   0.1858   1.0000
   7.000   0.9194   0.01683   0.00859  -0.0182   0.1000   1.0000
   7.250   0.9256   0.01827   0.00981  -0.0147   0.0721   1.0000
   7.500   0.9344   0.01941   0.01091  -0.0115   0.0597   1.0000
   7.750   0.9470   0.02022   0.01179  -0.0089   0.0533   1.0000
   8.000   0.9534   0.02146   0.01300  -0.0055   0.0487   1.0000
   8.250   0.9648   0.02234   0.01396  -0.0027   0.0463   1.0000
   8.500   0.9755   0.02328   0.01493   0.0001   0.0442   1.0000
   8.750   0.9857   0.02430   0.01596   0.0028   0.0427   1.0000
   9.000   0.9958   0.02558   0.01722   0.0055   0.0414   1.0000
   9.250   1.0097   0.02737   0.01901   0.0075   0.0401   1.0000
   9.500   1.0262   0.02856   0.02031   0.0093   0.0395   1.0000
   9.750   1.0433   0.02986   0.02173   0.0108   0.0390   1.0000
  10.000   1.0595   0.03120   0.02320   0.0125   0.0383   1.0000
  10.250   1.0752   0.03264   0.02479   0.0141   0.0376   1.0000
  10.500   1.0896   0.03419   0.02651   0.0159   0.0369   1.0000
  10.750   1.1029   0.03601   0.02851   0.0177   0.0365   1.0000
  11.000   1.1143   0.03805   0.03077   0.0197   0.0365   1.0000
  11.250   1.1219   0.04030   0.03327   0.0221   0.0365   1.0000
  11.500   1.1250   0.04269   0.03592   0.0248   0.0366   1.0000
  11.750   1.1212   0.04506   0.03855   0.0285   0.0368   1.0000
  12.000   1.1140   0.04754   0.04127   0.0322   0.0371   1.0000
  12.250   1.1037   0.05027   0.04424   0.0355   0.0373   1.0000
  12.500   1.0919   0.05328   0.04748   0.0381   0.0378   1.0000
  12.750   1.0774   0.05660   0.05102   0.0402   0.0381   1.0000
  13.000   1.0608   0.06028   0.05491   0.0414   0.0385   1.0000
  13.250   1.0428   0.06437   0.05919   0.0419   0.0388   1.0000
  13.500   1.0251   0.06895   0.06393   0.0416   0.0392   1.0000
  13.750   1.0059   0.07414   0.06927   0.0407   0.0396   1.0000
  14.000   1.0079   0.07815   0.07336   0.0407   0.0407   1.0000
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