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M6 (65%) (m665-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: M6 (65%) (m665-il)
Reynolds number: 500,000
Max Cl/Cd: 61.91 at α=3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m665-il-500000-n5.txt
Download as CSV file: xf-m665-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: M6 (65%)                                        
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5932   0.08395   0.08163  -0.0111   1.0000   0.0080
  -9.250  -0.6029   0.07839   0.07611  -0.0149   1.0000   0.0082
  -9.000  -0.6265   0.07106   0.06881  -0.0204   1.0000   0.0080
  -8.750  -0.6469   0.06444   0.06214  -0.0223   1.0000   0.0080
  -8.500  -0.6563   0.05860   0.05619  -0.0234   1.0000   0.0080
  -8.250  -0.7488   0.03079   0.02716  -0.0180   1.0000   0.0080
  -8.000  -0.7540   0.02490   0.02051  -0.0136   1.0000   0.0080
  -7.750  -0.7438   0.02215   0.01733  -0.0109   1.0000   0.0081
  -7.500  -0.7270   0.02088   0.01586  -0.0092   1.0000   0.0082
  -7.250  -0.7083   0.01992   0.01477  -0.0077   1.0000   0.0083
  -7.000  -0.6880   0.01931   0.01408  -0.0064   1.0000   0.0085
  -6.750  -0.6680   0.01862   0.01328  -0.0050   1.0000   0.0088
  -6.500  -0.6492   0.01755   0.01203  -0.0034   1.0000   0.0091
  -6.250  -0.6303   0.01649   0.01075  -0.0016   1.0000   0.0093
  -6.000  -0.6081   0.01542   0.00950  -0.0006   0.9992   0.0095
  -5.500  -0.5463   0.01354   0.00730  -0.0023   0.9892   0.0102
  -5.250  -0.5153   0.01288   0.00651  -0.0030   0.9829   0.0107
  -5.000  -0.4838   0.01215   0.00569  -0.0039   0.9762   0.0114
  -4.750  -0.4516   0.01167   0.00517  -0.0050   0.9677   0.0123
  -4.500  -0.4177   0.01124   0.00469  -0.0064   0.9580   0.0133
  -4.250  -0.3820   0.01086   0.00423  -0.0082   0.9461   0.0141
  -4.000  -0.3456   0.01048   0.00381  -0.0101   0.9306   0.0150
  -3.750  -0.3109   0.01022   0.00351  -0.0116   0.9108   0.0162
  -3.500  -0.2808   0.01002   0.00323  -0.0120   0.8875   0.0174
  -3.250  -0.2538   0.00987   0.00296  -0.0117   0.8636   0.0184
  -3.000  -0.2284   0.00971   0.00270  -0.0111   0.8407   0.0190
  -2.750  -0.2035   0.00956   0.00246  -0.0103   0.8199   0.0203
  -2.500  -0.1784   0.00945   0.00227  -0.0097   0.8001   0.0220
  -2.250  -0.1532   0.00936   0.00209  -0.0090   0.7818   0.0249
  -2.000  -0.1281   0.00924   0.00192  -0.0084   0.7647   0.0297
  -1.750  -0.1029   0.00915   0.00176  -0.0077   0.7484   0.0337
  -1.250  -0.0525   0.00891   0.00150  -0.0065   0.7184   0.0612
  -1.000  -0.0277   0.00874   0.00140  -0.0058   0.7043   0.0955
  -0.750  -0.0027   0.00859   0.00132  -0.0053   0.6909   0.1322
  -0.500   0.0223   0.00845   0.00125  -0.0047   0.6779   0.1701
  -0.250   0.0459   0.00815   0.00119  -0.0039   0.6657   0.2560
   0.000   0.0675   0.00769   0.00112  -0.0028   0.6540   0.3895
   0.250   0.0689   0.00613   0.00105   0.0029   0.6439   0.8118
   0.500   0.1540   0.00620   0.00140  -0.0094   0.6291   0.9370
   0.750   0.1967   0.00655   0.00170  -0.0122   0.6163   0.9617
   1.000   0.2406   0.00683   0.00191  -0.0154   0.6024   0.9730
   1.250   0.2762   0.00699   0.00199  -0.0171   0.5840   0.9782
   1.500   0.3076   0.00707   0.00199  -0.0179   0.5634   0.9801
   1.750   0.3378   0.00715   0.00201  -0.0185   0.5462   0.9823
   2.000   0.3665   0.00724   0.00206  -0.0187   0.5310   0.9849
   2.250   0.3962   0.00734   0.00209  -0.0191   0.5111   0.9868
   2.500   0.4275   0.00743   0.00212  -0.0200   0.4893   0.9882
   2.750   0.4577   0.00755   0.00217  -0.0206   0.4629   0.9899
   3.000   0.4860   0.00785   0.00223  -0.0210   0.4044   0.9918
   3.250   0.5129   0.00832   0.00235  -0.0212   0.3244   0.9937
   3.500   0.5396   0.00890   0.00254  -0.0214   0.2337   0.9953
   3.750   0.5672   0.00951   0.00279  -0.0219   0.1532   0.9968
   4.000   0.5948   0.01011   0.00307  -0.0224   0.0836   0.9983
   4.250   0.6235   0.01051   0.00333  -0.0229   0.0519   0.9996
   4.500   0.6477   0.01090   0.00362  -0.0224   0.0299   1.0000
   4.750   0.6699   0.01119   0.00390  -0.0214   0.0230   1.0000
   5.000   0.6919   0.01151   0.00421  -0.0203   0.0188   1.0000
   5.250   0.7140   0.01184   0.00457  -0.0192   0.0170   1.0000
   5.500   0.7360   0.01215   0.00494  -0.0181   0.0161   1.0000
   5.750   0.7579   0.01250   0.00533  -0.0170   0.0155   1.0000
   6.000   0.7794   0.01287   0.00576  -0.0159   0.0149   1.0000
   6.250   0.8005   0.01328   0.00621  -0.0147   0.0143   1.0000
   6.500   0.8213   0.01372   0.00671  -0.0134   0.0137   1.0000
   6.750   0.8414   0.01424   0.00728  -0.0121   0.0132   1.0000
   7.000   0.8608   0.01483   0.00793  -0.0106   0.0130   1.0000
   7.250   0.8787   0.01557   0.00874  -0.0089   0.0126   1.0000
   7.500   0.8954   0.01647   0.00974  -0.0071   0.0123   1.0000
   7.750   0.9119   0.01738   0.01074  -0.0052   0.0121   1.0000
   8.000   0.9298   0.01814   0.01159  -0.0035   0.0120   1.0000
   8.250   0.9470   0.01900   0.01255  -0.0018   0.0119   1.0000
   8.500   0.9641   0.01988   0.01354  -0.0001   0.0118   1.0000
   8.750   0.9832   0.02040   0.01414   0.0012   0.0114   1.0000
   9.000   1.0001   0.02126   0.01512   0.0029   0.0112   1.0000
   9.250   1.0170   0.02205   0.01601   0.0045   0.0108   1.0000
   9.500   1.0325   0.02308   0.01716   0.0063   0.0106   1.0000
   9.750   1.0468   0.02426   0.01849   0.0082   0.0105   1.0000
  10.000   1.0617   0.02519   0.01956   0.0099   0.0102   1.0000
  10.250   1.0752   0.02624   0.02074   0.0118   0.0099   1.0000
  10.500   1.0887   0.02712   0.02173   0.0136   0.0096   1.0000
  10.750   1.1022   0.02778   0.02245   0.0154   0.0093   1.0000
  11.000   1.1134   0.02867   0.02343   0.0174   0.0091   1.0000
  11.250   1.1221   0.02971   0.02456   0.0196   0.0088   1.0000
  11.500   1.1242   0.03120   0.02621   0.0228   0.0087   1.0000
  11.750   1.1195   0.03299   0.02815   0.0264   0.0085   1.0000
  12.000   1.1169   0.03473   0.03007   0.0293   0.0083   1.0000
  12.250   1.1186   0.03621   0.03174   0.0311   0.0081   1.0000
  12.500   1.1145   0.03853   0.03425   0.0327   0.0081   1.0000
  12.750   1.1115   0.04093   0.03683   0.0335   0.0079   1.0000
  13.000   1.1035   0.04420   0.04031   0.0337   0.0078   1.0000
  13.250   1.0977   0.04746   0.04375   0.0331   0.0076   1.0000
  13.500   1.0840   0.05213   0.04864   0.0316   0.0075   1.0000
  13.750   1.0642   0.05815   0.05488   0.0288   0.0075   1.0000
  14.000   1.0518   0.06350   0.06038   0.0259   0.0074   1.0000
  14.250   1.0261   0.07168   0.06876   0.0210   0.0075   1.0000
  14.500   1.0032   0.08010   0.07734   0.0157   0.0075   1.0000
  14.750   0.9739   0.09067   0.08804   0.0091   0.0076   1.0000
  15.000   0.9356   0.10434   0.10185   0.0013   0.0079   1.0000
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