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OAF117 AIRFOIL (oaf117-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: OAF117 AIRFOIL (oaf117-il)
Reynolds number: 1,000,000
Max Cl/Cd: 89.71 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-oaf117-il-1000000-n5.txt
Download as CSV file: xf-oaf117-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: OAF117 AIRFOIL                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -16.250  -1.2997   0.07607   0.07291  -0.0002   1.0000   0.0123
 -16.000  -1.3692   0.06130   0.05792  -0.0096   1.0000   0.0122
 -15.750  -1.4288   0.04765   0.04403  -0.0195   1.0000   0.0120
 -15.500  -1.4612   0.03535   0.03143  -0.0338   1.0000   0.0120
 -15.250  -1.4512   0.03188   0.02778  -0.0379   1.0000   0.0121
 -15.000  -1.4359   0.02992   0.02569  -0.0392   1.0000   0.0123
 -14.750  -1.4191   0.02807   0.02373  -0.0403   1.0000   0.0126
 -14.500  -1.3994   0.02664   0.02222  -0.0409   1.0000   0.0129
 -14.250  -1.3780   0.02544   0.02094  -0.0414   1.0000   0.0133
 -14.000  -1.3553   0.02439   0.01982  -0.0418   1.0000   0.0136
 -13.750  -1.3316   0.02344   0.01879  -0.0422   1.0000   0.0140
 -13.500  -1.3072   0.02258   0.01786  -0.0425   1.0000   0.0143
 -13.250  -1.2821   0.02180   0.01701  -0.0428   1.0000   0.0147
 -13.000  -1.2566   0.02105   0.01619  -0.0431   1.0000   0.0151
 -12.750  -1.2310   0.02023   0.01531  -0.0434   1.0000   0.0156
 -12.500  -1.2047   0.01953   0.01457  -0.0437   1.0000   0.0161
 -12.250  -1.1780   0.01889   0.01388  -0.0440   1.0000   0.0166
 -12.000  -1.1509   0.01830   0.01324  -0.0443   1.0000   0.0171
 -11.750  -1.1235   0.01775   0.01263  -0.0446   1.0000   0.0176
 -11.500  -1.0958   0.01724   0.01206  -0.0448   1.0000   0.0179
 -11.250  -1.0681   0.01665   0.01143  -0.0452   1.0000   0.0186
 -11.000  -1.0401   0.01614   0.01090  -0.0455   1.0000   0.0193
 -10.750  -1.0119   0.01568   0.01041  -0.0458   1.0000   0.0200
 -10.500  -0.9834   0.01526   0.00995  -0.0460   1.0000   0.0207
 -10.250  -0.9548   0.01487   0.00951  -0.0463   1.0000   0.0213
 -10.000  -0.9261   0.01440   0.00902  -0.0466   1.0000   0.0221
  -9.750  -0.8973   0.01399   0.00860  -0.0469   1.0000   0.0230
  -9.500  -0.8683   0.01363   0.00822  -0.0472   1.0000   0.0239
  -9.250  -0.8391   0.01329   0.00785  -0.0475   1.0000   0.0247
  -9.000  -0.8099   0.01294   0.00747  -0.0478   1.0000   0.0255
  -8.750  -0.7806   0.01258   0.00710  -0.0481   1.0000   0.0266
  -8.500  -0.7511   0.01226   0.00677  -0.0484   1.0000   0.0278
  -8.250  -0.7216   0.01198   0.00647  -0.0487   1.0000   0.0289
  -8.000  -0.6920   0.01168   0.00615  -0.0490   1.0000   0.0299
  -7.750  -0.6617   0.01140   0.00587  -0.0495   0.9747   0.0313
  -7.500  -0.6353   0.01132   0.00570  -0.0489   0.9237   0.0327
  -7.250  -0.6087   0.01121   0.00549  -0.0484   0.8926   0.0340
  -7.000  -0.5807   0.01104   0.00523  -0.0482   0.8658   0.0357
  -6.750  -0.5522   0.01088   0.00499  -0.0482   0.8411   0.0375
  -6.500  -0.5232   0.01075   0.00476  -0.0482   0.8180   0.0393
  -6.250  -0.4939   0.01059   0.00453  -0.0483   0.7954   0.0415
  -6.000  -0.4644   0.01044   0.00431  -0.0485   0.7728   0.0440
  -5.750  -0.4349   0.01034   0.00410  -0.0487   0.7507   0.0461
  -5.500  -0.4052   0.01018   0.00389  -0.0489   0.7289   0.0498
  -5.250  -0.3754   0.01006   0.00371  -0.0491   0.7092   0.0533
  -5.000  -0.3456   0.00991   0.00352  -0.0494   0.6899   0.0583
  -4.750  -0.3157   0.00979   0.00335  -0.0496   0.6705   0.0640
  -4.500  -0.2857   0.00965   0.00317  -0.0499   0.6513   0.0723
  -4.250  -0.2557   0.00950   0.00302  -0.0502   0.6345   0.0832
  -4.000  -0.2257   0.00935   0.00288  -0.0506   0.6204   0.0969
  -3.750  -0.1956   0.00922   0.00276  -0.0509   0.6065   0.1105
  -3.500  -0.1657   0.00915   0.00266  -0.0511   0.5919   0.1199
  -3.250  -0.1357   0.00907   0.00255  -0.0514   0.5774   0.1299
  -3.000  -0.1057   0.00899   0.00246  -0.0516   0.5630   0.1386
  -2.750  -0.0757   0.00892   0.00238  -0.0518   0.5504   0.1488
  -2.500  -0.0456   0.00883   0.00231  -0.0521   0.5397   0.1640
  -2.250  -0.0156   0.00877   0.00225  -0.0524   0.5287   0.1776
  -2.000   0.0144   0.00870   0.00220  -0.0526   0.5189   0.1904
  -1.750   0.0444   0.00864   0.00215  -0.0529   0.5085   0.2044
  -1.500   0.0745   0.00854   0.00211  -0.0532   0.4979   0.2286
  -1.250   0.1046   0.00848   0.00208  -0.0534   0.4870   0.2488
  -1.000   0.1345   0.00846   0.00206  -0.0537   0.4765   0.2627
  -0.750   0.1645   0.00843   0.00204  -0.0539   0.4674   0.2785
  -0.500   0.1944   0.00843   0.00204  -0.0541   0.4569   0.2924
  -0.250   0.2243   0.00842   0.00204  -0.0543   0.4457   0.3056
   0.000   0.2542   0.00843   0.00205  -0.0545   0.4345   0.3188
   0.250   0.2841   0.00845   0.00206  -0.0548   0.4205   0.3336
   0.500   0.3140   0.00849   0.00208  -0.0550   0.4061   0.3477
   0.750   0.3438   0.00852   0.00211  -0.0552   0.3937   0.3631
   1.000   0.3736   0.00856   0.00215  -0.0554   0.3827   0.3762
   1.250   0.4034   0.00860   0.00219  -0.0556   0.3712   0.3896
   1.500   0.4332   0.00864   0.00224  -0.0558   0.3601   0.4047
   1.750   0.4630   0.00869   0.00229  -0.0560   0.3488   0.4188
   2.000   0.4927   0.00876   0.00235  -0.0562   0.3383   0.4317
   2.250   0.5224   0.00882   0.00243  -0.0564   0.3267   0.4485
   2.500   0.5521   0.00887   0.00251  -0.0566   0.3153   0.4687
   2.750   0.5817   0.00894   0.00259  -0.0568   0.3045   0.4869
   3.000   0.6113   0.00904   0.00269  -0.0570   0.2911   0.5037
   3.250   0.6409   0.00913   0.00279  -0.0572   0.2792   0.5249
   3.500   0.6705   0.00922   0.00291  -0.0575   0.2683   0.5482
   3.750   0.7000   0.00931   0.00304  -0.0577   0.2570   0.5766
   4.000   0.7294   0.00941   0.00318  -0.0579   0.2413   0.6125
   4.250   0.7588   0.00957   0.00336  -0.0582   0.2173   0.6575
   4.500   0.7879   0.00971   0.00356  -0.0585   0.1961   0.7171
   4.750   0.8166   0.00980   0.00377  -0.0586   0.1784   0.7880
   5.000   0.8409   0.00970   0.00394  -0.0576   0.1650   0.9096
   5.250   0.8671   0.00978   0.00403  -0.0571   0.1522   1.0000
   5.500   0.8960   0.01006   0.00424  -0.0572   0.1395   1.0000
   5.750   0.9249   0.01036   0.00446  -0.0574   0.1269   1.0000
   6.000   0.9536   0.01066   0.00469  -0.0576   0.1145   1.0000
   6.250   0.9823   0.01095   0.00493  -0.0577   0.1034   1.0000
   6.500   1.0107   0.01130   0.00521  -0.0579   0.0907   1.0000
   6.750   1.0389   0.01168   0.00550  -0.0580   0.0786   1.0000
   7.000   1.0671   0.01204   0.00580  -0.0581   0.0688   1.0000
   7.250   1.0951   0.01242   0.00613  -0.0582   0.0600   1.0000
   7.500   1.1230   0.01278   0.00645  -0.0582   0.0531   1.0000
   7.750   1.1508   0.01314   0.00678  -0.0583   0.0479   1.0000
   8.000   1.1784   0.01351   0.00713  -0.0583   0.0434   1.0000
   8.250   1.2059   0.01387   0.00747  -0.0583   0.0398   1.0000
   8.500   1.2333   0.01425   0.00784  -0.0583   0.0367   1.0000
   8.750   1.2605   0.01461   0.00821  -0.0582   0.0343   1.0000
   9.000   1.2874   0.01502   0.00860  -0.0582   0.0321   1.0000
   9.250   1.3143   0.01538   0.00898  -0.0581   0.0306   1.0000
   9.500   1.3408   0.01579   0.00940  -0.0580   0.0289   1.0000
   9.750   1.3670   0.01624   0.00985  -0.0578   0.0273   1.0000
  10.000   1.3933   0.01664   0.01027  -0.0577   0.0261   1.0000
  10.250   1.4191   0.01708   0.01073  -0.0575   0.0249   1.0000
  10.500   1.4444   0.01758   0.01123  -0.0572   0.0238   1.0000
  10.750   1.4695   0.01807   0.01175  -0.0570   0.0229   1.0000
  11.000   1.4945   0.01853   0.01225  -0.0567   0.0222   1.0000
  11.250   1.5190   0.01904   0.01279  -0.0564   0.0215   1.0000
  11.500   1.5429   0.01958   0.01336  -0.0560   0.0207   1.0000
  11.750   1.5661   0.02019   0.01399  -0.0555   0.0200   1.0000
  12.000   1.5886   0.02083   0.01467  -0.0550   0.0194   1.0000
  12.250   1.6113   0.02140   0.01529  -0.0544   0.0190   1.0000
  12.500   1.6331   0.02202   0.01595  -0.0538   0.0184   1.0000
  12.750   1.6541   0.02269   0.01666  -0.0531   0.0179   1.0000
  13.000   1.6740   0.02341   0.01744  -0.0523   0.0174   1.0000
  13.250   1.6925   0.02421   0.01827  -0.0514   0.0170   1.0000
  13.500   1.7091   0.02511   0.01922  -0.0503   0.0166   1.0000
  13.750   1.7236   0.02609   0.02026  -0.0489   0.0162   1.0000
  14.000   1.7371   0.02701   0.02125  -0.0474   0.0160   1.0000
  14.250   1.7478   0.02805   0.02238  -0.0457   0.0158   1.0000
  14.500   1.7513   0.02936   0.02377  -0.0432   0.0156   1.0000
  14.750   1.7544   0.03104   0.02555  -0.0416   0.0154   1.0000
  15.000   1.7579   0.03306   0.02766  -0.0408   0.0152   1.0000
  15.250   1.7608   0.03542   0.03011  -0.0405   0.0150   1.0000
  15.500   1.7626   0.03814   0.03293  -0.0408   0.0148   1.0000
  15.750   1.7627   0.04124   0.03613  -0.0413   0.0146   1.0000
  16.000   1.7608   0.04475   0.03974  -0.0422   0.0144   1.0000
  16.250   1.7563   0.04869   0.04379  -0.0433   0.0142   1.0000
  16.500   1.7486   0.05314   0.04834  -0.0447   0.0141   1.0000
  16.750   1.7377   0.05809   0.05341  -0.0463   0.0140   1.0000
  17.000   1.7234   0.06354   0.05898  -0.0481   0.0138   1.0000
  17.250   1.7063   0.06947   0.06504  -0.0501   0.0138   1.0000
  17.500   1.6862   0.07588   0.07158  -0.0523   0.0137   1.0000
  17.750   1.6646   0.08274   0.07857  -0.0549   0.0136   1.0000
  18.000   1.6424   0.08988   0.08584  -0.0577   0.0136   1.0000
  18.250   1.6198   0.09731   0.09339  -0.0608   0.0135   1.0000
  18.500   1.5965   0.10499   0.10120  -0.0641   0.0134   1.0000
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