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M6 (65%) (m665-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: M6 (65%) (m665-il)
Reynolds number: 1,000,000
Max Cl/Cd: 78.56 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-m665-il-1000000.txt
Download as CSV file: xf-m665-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4625   0.08014   0.07859  -0.0120   1.0000   0.0126
  -9.000  -0.4679   0.07519   0.07365  -0.0138   1.0000   0.0128
  -8.750  -0.4767   0.06952   0.06801  -0.0163   1.0000   0.0138
  -8.500  -0.4865   0.06438   0.06288  -0.0188   1.0000   0.0137
  -8.250  -0.5049   0.05899   0.05751  -0.0230   1.0000   0.0136
  -8.000  -0.5237   0.05480   0.05330  -0.0235   1.0000   0.0132
  -7.750  -0.5364   0.04924   0.04768  -0.0245   1.0000   0.0135
  -7.250  -0.6359   0.03775   0.03533  -0.0185   1.0000   0.0100
  -7.000  -0.6934   0.01921   0.01514  -0.0054   1.0000   0.0094
  -6.750  -0.6803   0.01713   0.01272  -0.0026   1.0000   0.0096
  -6.500  -0.6625   0.01608   0.01150  -0.0006   1.0000   0.0099
  -6.250  -0.6453   0.01492   0.01015   0.0015   1.0000   0.0102
  -6.000  -0.6257   0.01437   0.00949   0.0032   1.0000   0.0106
  -5.750  -0.5959   0.01252   0.00738   0.0025   0.9980   0.0114
  -5.500  -0.5615   0.01195   0.00676   0.0009   0.9955   0.0121
  -5.250  -0.5276   0.01159   0.00637  -0.0005   0.9926   0.0131
  -5.000  -0.4942   0.01115   0.00587  -0.0018   0.9887   0.0141
  -4.750  -0.4607   0.01036   0.00499  -0.0031   0.9848   0.0155
  -4.500  -0.4282   0.01005   0.00469  -0.0042   0.9791   0.0170
  -4.250  -0.3935   0.00981   0.00445  -0.0057   0.9730   0.0186
  -4.000  -0.3570   0.00967   0.00429  -0.0076   0.9660   0.0197
  -3.750  -0.3214   0.00892   0.00350  -0.0094   0.9559   0.0221
  -3.500  -0.2854   0.00866   0.00321  -0.0112   0.9394   0.0239
  -3.250  -0.2533   0.00848   0.00297  -0.0121   0.9153   0.0258
  -3.000  -0.2261   0.00839   0.00278  -0.0118   0.8891   0.0267
  -2.750  -0.2032   0.00798   0.00221  -0.0106   0.8635   0.0298
  -2.500  -0.1789   0.00782   0.00196  -0.0096   0.8401   0.0326
  -2.250  -0.1541   0.00772   0.00177  -0.0089   0.8183   0.0355
  -2.000  -0.1295   0.00759   0.00155  -0.0080   0.7978   0.0399
  -1.750  -0.1046   0.00748   0.00139  -0.0073   0.7798   0.0466
  -1.500  -0.0803   0.00727   0.00126  -0.0065   0.7628   0.0808
  -1.250  -0.0567   0.00698   0.00116  -0.0057   0.7466   0.1491
  -1.000  -0.0335   0.00669   0.00107  -0.0048   0.7313   0.2307
  -0.750  -0.0126   0.00619   0.00098  -0.0035   0.7171   0.3735
  -0.500  -0.0031   0.00509   0.00085   0.0002   0.7040   0.6769
  -0.250   0.0105   0.00443   0.00087   0.0037   0.6918   0.8779
   0.000   0.0673   0.00448   0.00100  -0.0026   0.6788   0.9341
   0.250   0.1132   0.00468   0.00114  -0.0065   0.6655   0.9524
   0.500   0.1448   0.00485   0.00125  -0.0071   0.6516   0.9608
   0.750   0.1828   0.00509   0.00141  -0.0091   0.6361   0.9680
   1.000   0.2248   0.00535   0.00159  -0.0121   0.6183   0.9741
   1.250   0.2736   0.00563   0.00180  -0.0166   0.6025   0.9794
   1.500   0.3087   0.00581   0.00194  -0.0181   0.5883   0.9844
   1.750   0.3478   0.00588   0.00194  -0.0206   0.5692   0.9859
   2.000   0.3811   0.00593   0.00194  -0.0218   0.5524   0.9872
   2.250   0.4133   0.00600   0.00194  -0.0229   0.5320   0.9887
   2.500   0.4443   0.00612   0.00195  -0.0237   0.4995   0.9904
   2.750   0.4741   0.00630   0.00197  -0.0243   0.4581   0.9924
   3.000   0.5028   0.00653   0.00204  -0.0246   0.4146   0.9942
   3.250   0.5334   0.00679   0.00208  -0.0255   0.3577   0.9954
   3.500   0.5631   0.00717   0.00217  -0.0263   0.2853   0.9967
   3.750   0.5923   0.00764   0.00232  -0.0270   0.2089   0.9981
   4.000   0.6209   0.00820   0.00254  -0.0276   0.1311   0.9994
   4.250   0.6457   0.00878   0.00282  -0.0274   0.0659   1.0000
   4.500   0.6666   0.00923   0.00309  -0.0262   0.0313   1.0000
   4.750   0.6887   0.00954   0.00338  -0.0251   0.0232   1.0000
   5.000   0.7109   0.00982   0.00366  -0.0240   0.0203   1.0000
   5.250   0.7321   0.01027   0.00419  -0.0227   0.0182   1.0000
   5.500   0.7544   0.01053   0.00447  -0.0216   0.0175   1.0000
   5.750   0.7761   0.01087   0.00486  -0.0205   0.0171   1.0000
   6.000   0.7978   0.01120   0.00523  -0.0193   0.0164   1.0000
   6.250   0.8190   0.01160   0.00569  -0.0181   0.0158   1.0000
   6.500   0.8396   0.01207   0.00620  -0.0167   0.0155   1.0000
   6.750   0.8598   0.01257   0.00676  -0.0154   0.0153   1.0000
   7.000   0.8795   0.01312   0.00737  -0.0139   0.0150   1.0000
   7.250   0.8990   0.01368   0.00799  -0.0124   0.0147   1.0000
   7.500   0.9177   0.01433   0.00869  -0.0108   0.0144   1.0000
   7.750   0.9356   0.01508   0.00950  -0.0091   0.0141   1.0000
   8.000   0.9527   0.01597   0.01045  -0.0073   0.0140   1.0000
   8.250   0.9653   0.01764   0.01223  -0.0048   0.0134   1.0000
   8.500   0.9811   0.01896   0.01369  -0.0029   0.0130   1.0000
   8.750   1.0018   0.01919   0.01399  -0.0017   0.0127   1.0000
   9.000   1.0197   0.02001   0.01491  -0.0001   0.0124   1.0000
   9.250   1.0374   0.02076   0.01575   0.0015   0.0119   1.0000
   9.500   1.0537   0.02175   0.01685   0.0032   0.0116   1.0000
   9.750   1.0701   0.02256   0.01775   0.0049   0.0112   1.0000
  10.000   1.0855   0.02350   0.01879   0.0067   0.0109   1.0000
  10.250   1.0994   0.02454   0.01995   0.0086   0.0107   1.0000
  10.500   1.1142   0.02519   0.02066   0.0103   0.0103   1.0000
  10.750   1.1265   0.02615   0.02169   0.0123   0.0100   1.0000
  11.000   1.1243   0.02930   0.02508   0.0157   0.0095   1.0000
  11.250   1.1263   0.03108   0.02710   0.0188   0.0092   1.0000
  11.500   1.1340   0.03202   0.02817   0.0213   0.0090   1.0000
  11.750   1.1339   0.03311   0.02939   0.0250   0.0088   1.0000
  12.000   1.1364   0.03386   0.03024   0.0280   0.0084   1.0000
  12.250   1.1365   0.03514   0.03163   0.0305   0.0082   1.0000
  12.500   1.1404   0.03618   0.03275   0.0322   0.0079   1.0000
  12.750   1.1324   0.03882   0.03556   0.0337   0.0078   1.0000
  13.000   1.1256   0.04160   0.03849   0.0343   0.0077   1.0000
  13.250   1.1163   0.04503   0.04207   0.0340   0.0076   1.0000
  13.500   1.1184   0.04724   0.04436   0.0333   0.0074   1.0000
  13.750   1.1121   0.05085   0.04809   0.0319   0.0073   1.0000
  14.000   1.0869   0.05772   0.05518   0.0287   0.0074   1.0000
  14.250   1.0759   0.06287   0.06045   0.0257   0.0073   1.0000
  14.750   0.7583   0.10206   0.10030   0.0107   0.0095   1.0000
  15.000   0.7461   0.10897   0.10728   0.0074   0.0096   1.0000
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