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M6 (85%) (m685-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: M6 (85%) (m685-il)
Reynolds number: 50,000
Max Cl/Cd: 34.25 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m685-il-50000-n5.txt
Download as CSV file: xf-m685-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.4998   0.11777   0.11043  -0.0162   1.0000   0.1253
  -9.750  -0.5028   0.10126   0.09390  -0.0248   1.0000   0.0684
  -9.500  -0.5011   0.09710   0.08978  -0.0260   1.0000   0.0679
  -9.250  -0.5012   0.09284   0.08556  -0.0274   1.0000   0.0671
  -9.000  -0.5034   0.08849   0.08127  -0.0293   1.0000   0.0660
  -8.750  -0.5105   0.08401   0.07684  -0.0311   1.0000   0.0647
  -8.500  -0.5212   0.07980   0.07266  -0.0318   1.0000   0.0635
  -8.250  -0.5338   0.07561   0.06847  -0.0318   1.0000   0.0624
  -8.000  -0.5457   0.07110   0.06390  -0.0315   1.0000   0.0612
  -7.750  -0.5576   0.06643   0.05909  -0.0306   1.0000   0.0600
  -7.500  -0.5691   0.06170   0.05408  -0.0288   1.0000   0.0589
  -7.000  -0.5780   0.05394   0.04559  -0.0234   1.0000   0.0578
  -6.750  -0.5750   0.05079   0.04216  -0.0207   1.0000   0.0578
  -6.500  -0.5696   0.04788   0.03906  -0.0181   1.0000   0.0582
  -6.250  -0.5601   0.04569   0.03678  -0.0159   1.0000   0.0593
  -6.000  -0.5508   0.04366   0.03461  -0.0135   1.0000   0.0607
  -5.750  -0.5421   0.04153   0.03224  -0.0108   1.0000   0.0622
  -5.500  -0.5330   0.03936   0.02976  -0.0080   1.0000   0.0636
  -5.250  -0.5229   0.03723   0.02730  -0.0052   1.0000   0.0647
  -5.000  -0.5116   0.03532   0.02501  -0.0025   1.0000   0.0664
  -4.750  -0.4991   0.03360   0.02282   0.0003   1.0000   0.0686
  -4.500  -0.4855   0.03211   0.02121   0.0023   1.0000   0.0708
  -4.250  -0.4716   0.03100   0.02002   0.0044   1.0000   0.0738
  -4.000  -0.4563   0.02992   0.01875   0.0063   1.0000   0.0773
  -3.750  -0.4170   0.02837   0.01675   0.0042   0.9917   0.0819
  -3.500  -0.3757   0.02704   0.01544   0.0012   0.9823   0.0888
  -3.250  -0.3299   0.02585   0.01402  -0.0021   0.9741   0.0975
  -3.000  -0.2856   0.02487   0.01294  -0.0054   0.9645   0.1108
  -2.750  -0.2446   0.02386   0.01200  -0.0082   0.9542   0.1298
  -2.500  -0.2050   0.02280   0.01111  -0.0108   0.9438   0.1708
  -2.250  -0.1074   0.01970   0.01131  -0.0218   0.9561   0.8907
  -2.000   0.0056   0.02016   0.01108  -0.0368   0.9682   1.0000
  -1.750   0.0499   0.02004   0.01065  -0.0407   0.9517   1.0000
  -1.500   0.0943   0.01991   0.01025  -0.0445   0.9361   1.0000
  -1.250   0.1364   0.01979   0.00991  -0.0477   0.9202   1.0000
  -1.000   0.1764   0.01968   0.00961  -0.0504   0.9042   1.0000
  -0.750   0.2138   0.01959   0.00935  -0.0525   0.8879   1.0000
  -0.500   0.2480   0.01955   0.00915  -0.0539   0.8717   1.0000
  -0.250   0.2790   0.01954   0.00901  -0.0546   0.8554   1.0000
   0.000   0.3072   0.01957   0.00893  -0.0547   0.8395   1.0000
   0.250   0.3332   0.01965   0.00891  -0.0543   0.8238   1.0000
   0.500   0.3576   0.01975   0.00893  -0.0536   0.8086   1.0000
   0.750   0.3810   0.01988   0.00899  -0.0527   0.7937   1.0000
   1.000   0.4038   0.02003   0.00909  -0.0517   0.7794   1.0000
   1.250   0.4263   0.02020   0.00921  -0.0506   0.7656   1.0000
   1.500   0.4487   0.02037   0.00935  -0.0495   0.7523   1.0000
   1.750   0.4716   0.02053   0.00948  -0.0483   0.7397   1.0000
   2.000   0.4929   0.02076   0.00971  -0.0470   0.7263   1.0000
   2.250   0.5142   0.02102   0.00998  -0.0458   0.7130   1.0000
   2.500   0.5361   0.02127   0.01027  -0.0446   0.7000   1.0000
   2.750   0.5583   0.02151   0.01054  -0.0434   0.6876   1.0000
   3.000   0.5812   0.02172   0.01075  -0.0422   0.6757   1.0000
   3.250   0.6022   0.02200   0.01112  -0.0408   0.6622   1.0000
   3.500   0.6227   0.02231   0.01148  -0.0394   0.6484   1.0000
   3.750   0.6434   0.02259   0.01183  -0.0379   0.6346   1.0000
   4.000   0.6641   0.02285   0.01216  -0.0363   0.6205   1.0000
   4.250   0.6848   0.02311   0.01251  -0.0347   0.6062   1.0000
   4.500   0.7054   0.02336   0.01284  -0.0331   0.5918   1.0000
   4.750   0.7260   0.02362   0.01318  -0.0315   0.5773   1.0000
   5.000   0.7464   0.02388   0.01356  -0.0298   0.5624   1.0000
   5.250   0.7666   0.02415   0.01394  -0.0281   0.5472   1.0000
   5.500   0.7863   0.02444   0.01436  -0.0263   0.5314   1.0000
   5.750   0.8049   0.02474   0.01481  -0.0244   0.5138   1.0000
   6.000   0.8225   0.02491   0.01508  -0.0221   0.4921   1.0000
   6.250   0.8388   0.02496   0.01518  -0.0194   0.4654   1.0000
   6.500   0.8532   0.02506   0.01531  -0.0165   0.4344   1.0000
   6.750   0.8668   0.02531   0.01558  -0.0136   0.4019   1.0000
   7.000   0.8785   0.02567   0.01587  -0.0105   0.3642   1.0000
   7.250   0.8870   0.02627   0.01634  -0.0072   0.3186   1.0000
   7.500   0.8929   0.02717   0.01705  -0.0038   0.2663   1.0000
   7.750   0.8947   0.02850   0.01802  -0.0002   0.2132   1.0000
   8.000   0.8939   0.03019   0.01936   0.0035   0.1685   1.0000
   8.250   0.8924   0.03200   0.02088   0.0070   0.1378   1.0000
   8.500   0.8927   0.03373   0.02249   0.0103   0.1179   1.0000
   8.750   0.8922   0.03546   0.02410   0.0136   0.1050   1.0000
   9.000   0.8899   0.03715   0.02570   0.0171   0.0965   1.0000
   9.250   0.8915   0.03879   0.02738   0.0200   0.0886   1.0000
   9.500   0.8940   0.04056   0.02911   0.0226   0.0828   1.0000
   9.750   0.9009   0.04221   0.03088   0.0247   0.0767   1.0000
  10.000   0.9091   0.04394   0.03255   0.0265   0.0724   1.0000
  10.250   0.9256   0.04556   0.03438   0.0281   0.0684   1.0000
  10.500   0.9388   0.04732   0.03634   0.0296   0.0644   1.0000
  10.750   0.9514   0.04912   0.03815   0.0309   0.0611   1.0000
  11.000   0.9661   0.05120   0.04037   0.0321   0.0587   1.0000
  11.250   0.9765   0.05362   0.04312   0.0334   0.0572   1.0000
  11.500   0.9821   0.05626   0.04606   0.0347   0.0559   1.0000
  11.750   0.9826   0.05908   0.04915   0.0359   0.0547   1.0000
  12.000   0.9802   0.06210   0.05240   0.0369   0.0539   1.0000
  12.250   0.9743   0.06536   0.05587   0.0375   0.0529   1.0000
  12.500   0.9662   0.06893   0.05964   0.0377   0.0523   1.0000
  12.750   0.9549   0.07300   0.06391   0.0373   0.0519   1.0000
  13.000   0.9414   0.07746   0.06855   0.0364   0.0515   1.0000
  13.250   0.9196   0.08335   0.07468   0.0342   0.0517   1.0000
  13.500   0.8884   0.09124   0.08281   0.0301   0.0523   1.0000
  13.750   0.8393   0.10392   0.09570   0.0223   0.0543   1.0000
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