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NACA 64(1)-212 MOD A (n64212ma-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: NACA 64(1)-212 MOD A (n64212ma-il)
Reynolds number: 1,000,000
Max Cl/Cd: 79.07 at α=8.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n64212ma-il-1000000-n5.txt
Download as CSV file: xf-n64212ma-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64(1)-212 MOD A                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.4618   0.10852   0.10667  -0.0223   1.0000   0.0121
 -11.500  -0.4569   0.10544   0.10360  -0.0237   1.0000   0.0123
 -10.000  -0.7572   0.02275   0.01849  -0.0586   0.8806   0.0174
  -9.750  -0.7406   0.02113   0.01664  -0.0576   0.8682   0.0176
  -9.500  -0.7190   0.02050   0.01588  -0.0567   0.8527   0.0178
  -9.250  -0.6962   0.01987   0.01516  -0.0561   0.8390   0.0179
  -9.000  -0.6728   0.01933   0.01451  -0.0555   0.8275   0.0180
  -8.750  -0.6489   0.01880   0.01388  -0.0550   0.8145   0.0181
  -8.500  -0.6246   0.01829   0.01327  -0.0545   0.8024   0.0183
  -8.250  -0.5999   0.01784   0.01272  -0.0540   0.7899   0.0185
  -8.000  -0.5750   0.01732   0.01209  -0.0536   0.7784   0.0187
  -7.500  -0.5252   0.01614   0.01067  -0.0527   0.7510   0.0192
  -7.250  -0.5002   0.01547   0.00985  -0.0523   0.7392   0.0194
  -7.000  -0.4747   0.01482   0.00908  -0.0519   0.7277   0.0197
  -6.750  -0.4490   0.01426   0.00839  -0.0515   0.7156   0.0199
  -6.500  -0.4231   0.01376   0.00778  -0.0511   0.7013   0.0201
  -6.250  -0.3971   0.01335   0.00724  -0.0507   0.6824   0.0203
  -6.000  -0.3712   0.01303   0.00677  -0.0503   0.6565   0.0205
  -5.500  -0.3196   0.01231   0.00577  -0.0495   0.6040   0.0208
  -5.250  -0.2940   0.01207   0.00539  -0.0491   0.5649   0.0211
  -5.000  -0.2687   0.01205   0.00511  -0.0487   0.4969   0.0213
  -4.750  -0.2492   0.01304   0.00512  -0.0477   0.1779   0.0215
  -4.500  -0.2230   0.01304   0.00491  -0.0474   0.1053   0.0218
  -4.250  -0.1958   0.01288   0.00471  -0.0472   0.1000   0.0221
  -4.000  -0.1684   0.01272   0.00452  -0.0470   0.0978   0.0225
  -3.750  -0.1411   0.01253   0.00429  -0.0469   0.0962   0.0229
  -3.500  -0.1138   0.01235   0.00407  -0.0467   0.0944   0.0232
  -3.250  -0.0863   0.01218   0.00386  -0.0465   0.0933   0.0235
  -3.000  -0.0587   0.01202   0.00368  -0.0464   0.0926   0.0237
  -2.750  -0.0310   0.01189   0.00351  -0.0463   0.0919   0.0240
  -2.500  -0.0033   0.01173   0.00333  -0.0461   0.0912   0.0242
  -2.250   0.0243   0.01157   0.00315  -0.0460   0.0905   0.0247
  -2.000   0.0521   0.01148   0.00305  -0.0459   0.0899   0.0251
  -1.750   0.0800   0.01142   0.00297  -0.0459   0.0893   0.0256
  -1.500   0.1079   0.01137   0.00290  -0.0458   0.0887   0.0261
  -1.250   0.1359   0.01132   0.00283  -0.0457   0.0883   0.0267
  -1.000   0.1640   0.01128   0.00278  -0.0456   0.0879   0.0274
  -0.750   0.1921   0.01124   0.00273  -0.0456   0.0875   0.0279
  -0.500   0.2201   0.01120   0.00268  -0.0455   0.0871   0.0287
  -0.250   0.2482   0.01118   0.00266  -0.0455   0.0867   0.0296
   0.000   0.2763   0.01119   0.00265  -0.0454   0.0864   0.0306
   0.250   0.3043   0.01120   0.00265  -0.0453   0.0860   0.0316
   0.500   0.3323   0.01121   0.00267  -0.0453   0.0857   0.0334
   0.750   0.3603   0.01123   0.00269  -0.0452   0.0854   0.0356
   1.000   0.3882   0.01126   0.00273  -0.0451   0.0851   0.0397
   1.250   0.4162   0.01129   0.00277  -0.0451   0.0843   0.0471
   1.500   0.4440   0.01133   0.00283  -0.0450   0.0834   0.0597
   1.750   0.4717   0.01051   0.00278  -0.0456   0.0828   0.3860
   2.000   0.4991   0.01004   0.00285  -0.0459   0.0823   0.5723
   2.250   0.5268   0.01002   0.00295  -0.0458   0.0818   0.6182
   2.500   0.5545   0.01003   0.00306  -0.0458   0.0811   0.6546
   2.750   0.5823   0.01008   0.00316  -0.0457   0.0802   0.6821
   3.000   0.6097   0.01012   0.00326  -0.0455   0.0792   0.7162
   3.250   0.6372   0.01020   0.00338  -0.0454   0.0784   0.7348
   3.500   0.6648   0.01030   0.00350  -0.0452   0.0776   0.7442
   3.750   0.6923   0.01042   0.00362  -0.0451   0.0763   0.7519
   4.000   0.7199   0.01054   0.00371  -0.0450   0.0743   0.7587
   4.250   0.7470   0.01067   0.00376  -0.0449   0.0562   0.7662
   4.500   0.7731   0.01092   0.00399  -0.0446   0.0531   0.7746
   5.000   0.8258   0.01134   0.00444  -0.0440   0.0506   0.7913
   5.250   0.8520   0.01154   0.00466  -0.0437   0.0496   0.8002
   5.500   0.8783   0.01174   0.00488  -0.0434   0.0483   0.8080
   5.750   0.9040   0.01196   0.00512  -0.0431   0.0470   0.8171
   6.000   0.9302   0.01214   0.00532  -0.0428   0.0458   0.8260
   6.250   0.9559   0.01232   0.00554  -0.0424   0.0435   0.8357
   6.500   0.9810   0.01258   0.00576  -0.0420   0.0337   0.8454
   6.750   1.0051   0.01286   0.00604  -0.0414   0.0313   0.8554
   7.000   1.0295   0.01314   0.00633  -0.0408   0.0303   0.8666
   7.250   1.0530   0.01341   0.00664  -0.0401   0.0296   0.8785
   7.500   1.0761   0.01371   0.00697  -0.0393   0.0289   0.8911
   8.000   1.1204   0.01422   0.00758  -0.0373   0.0283   0.9241
   8.250   1.1405   0.01446   0.00788  -0.0359   0.0280   0.9480
   8.500   1.1670   0.01476   0.00822  -0.0359   0.0277   1.0000
   8.750   1.1903   0.01512   0.00860  -0.0353   0.0274   1.0000
   9.000   1.2132   0.01550   0.00899  -0.0347   0.0272   1.0000
   9.250   1.2354   0.01591   0.00941  -0.0340   0.0269   1.0000
   9.500   1.2570   0.01634   0.00985  -0.0332   0.0267   1.0000
   9.750   1.2777   0.01682   0.01034  -0.0323   0.0264   1.0000
  10.000   1.2976   0.01731   0.01086  -0.0313   0.0260   1.0000
  10.250   1.3180   0.01772   0.01129  -0.0303   0.0258   1.0000
  10.500   1.3362   0.01814   0.01174  -0.0290   0.0256   1.0000
  10.750   1.3528   0.01859   0.01221  -0.0274   0.0253   1.0000
  11.000   1.3683   0.01908   0.01274  -0.0257   0.0252   1.0000
  11.250   1.3832   0.01962   0.01331  -0.0240   0.0250   1.0000
  11.500   1.3978   0.02019   0.01392  -0.0224   0.0249   1.0000
  11.750   1.4121   0.02080   0.01457  -0.0208   0.0247   1.0000
  12.000   1.4257   0.02147   0.01528  -0.0193   0.0246   1.0000
  12.250   1.4391   0.02218   0.01604  -0.0178   0.0244   1.0000
  12.500   1.4518   0.02296   0.01686  -0.0164   0.0243   1.0000
  12.750   1.4641   0.02379   0.01774  -0.0150   0.0242   1.0000
  13.000   1.4756   0.02471   0.01870  -0.0136   0.0240   1.0000
  13.250   1.4863   0.02570   0.01975  -0.0123   0.0239   1.0000
  13.500   1.4962   0.02680   0.02089  -0.0110   0.0237   1.0000
  13.750   1.5048   0.02802   0.02217  -0.0098   0.0236   1.0000
  14.000   1.5125   0.02936   0.02357  -0.0086   0.0235   1.0000
  14.250   1.5176   0.03096   0.02523  -0.0075   0.0233   1.0000
  14.500   1.5264   0.03231   0.02665  -0.0067   0.0232   1.0000
  14.750   1.5353   0.03369   0.02810  -0.0060   0.0231   1.0000
  15.000   1.5428   0.03524   0.02972  -0.0053   0.0230   1.0000
  15.250   1.5493   0.03693   0.03149  -0.0047   0.0229   1.0000
  15.500   1.5548   0.03878   0.03341  -0.0043   0.0227   1.0000
  15.750   1.5590   0.04081   0.03552  -0.0040   0.0226   1.0000
  16.000   1.5622   0.04301   0.03780  -0.0038   0.0225   1.0000
  16.250   1.5640   0.04543   0.04031  -0.0038   0.0224   1.0000
  16.500   1.5647   0.04808   0.04305  -0.0040   0.0223   1.0000
  16.750   1.5656   0.05083   0.04589  -0.0043   0.0221   1.0000
  17.000   1.5633   0.05409   0.04923  -0.0050   0.0220   1.0000
  17.250   1.5607   0.05751   0.05276  -0.0059   0.0219   1.0000
  17.500   1.5562   0.06135   0.05669  -0.0071   0.0218   1.0000
  17.750   1.5492   0.06572   0.06118  -0.0087   0.0217   1.0000
  18.000   1.5416   0.07038   0.06594  -0.0106   0.0216   1.0000
  18.250   1.5301   0.07587   0.07156  -0.0130   0.0215   1.0000
  18.500   1.5126   0.08267   0.07851  -0.0165   0.0215   1.0000
  18.750   1.4934   0.09024   0.08623  -0.0206   0.0214   1.0000
  19.000   1.4657   0.09975   0.09592  -0.0260   0.0214   1.0000
  19.250   1.4343   0.11034   0.10670  -0.0321   0.0214   1.0000
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