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NACA M15 AIRFOIL (m15-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NACA M15 AIRFOIL (m15-il)
Reynolds number: 500,000
Max Cl/Cd: 98.69 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m15-il-500000-n5.txt
Download as CSV file: xf-m15-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M15 AIRFOIL                                
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4266   0.08724   0.08490  -0.0341   0.9481   0.0213
  -9.250  -0.4981   0.06414   0.06156  -0.0517   0.8772   0.0225
  -9.000  -0.5065   0.05753   0.05476  -0.0553   0.8573   0.0227
  -8.750  -0.5083   0.05162   0.04863  -0.0573   0.8406   0.0229
  -8.500  -0.5081   0.04533   0.04206  -0.0584   0.8259   0.0233
  -8.250  -0.5088   0.03797   0.03430  -0.0586   0.8125   0.0239
  -8.000  -0.5206   0.02792   0.02328  -0.0566   0.8001   0.0248
  -7.750  -0.5059   0.02501   0.01990  -0.0554   0.7875   0.0252
  -7.500  -0.4869   0.02302   0.01754  -0.0544   0.7756   0.0255
  -7.250  -0.4656   0.02150   0.01569  -0.0537   0.7647   0.0258
  -7.000  -0.4424   0.02033   0.01425  -0.0531   0.7543   0.0262
  -6.750  -0.4179   0.01945   0.01313  -0.0526   0.7450   0.0266
  -6.500  -0.3930   0.01868   0.01215  -0.0522   0.7352   0.0268
  -6.250  -0.3675   0.01795   0.01122  -0.0518   0.7251   0.0270
  -6.000  -0.3424   0.01707   0.01013  -0.0514   0.7151   0.0272
  -5.750  -0.3171   0.01614   0.00905  -0.0511   0.7052   0.0276
  -5.500  -0.2910   0.01550   0.00830  -0.0509   0.6964   0.0278
  -5.250  -0.2646   0.01498   0.00768  -0.0507   0.6874   0.0281
  -5.000  -0.2378   0.01453   0.00714  -0.0505   0.6793   0.0284
  -4.750  -0.2109   0.01411   0.00665  -0.0503   0.6717   0.0288
  -4.500  -0.1838   0.01373   0.00619  -0.0502   0.6658   0.0291
  -4.250  -0.1566   0.01335   0.00576  -0.0501   0.6602   0.0295
  -4.000  -0.1294   0.01302   0.00535  -0.0499   0.6549   0.0298
  -3.750  -0.1020   0.01272   0.00500  -0.0498   0.6499   0.0304
  -3.500  -0.0745   0.01243   0.00468  -0.0497   0.6446   0.0310
  -3.250  -0.0471   0.01217   0.00437  -0.0496   0.6397   0.0315
  -3.000  -0.0197   0.01192   0.00406  -0.0495   0.6353   0.0319
  -2.750   0.0080   0.01168   0.00379  -0.0495   0.6305   0.0323
  -2.500   0.0357   0.01148   0.00355  -0.0494   0.6253   0.0326
  -2.250   0.0628   0.01120   0.00324  -0.0493   0.6206   0.0334
  -2.000   0.0905   0.01099   0.00303  -0.0492   0.6163   0.0342
  -1.750   0.1184   0.01082   0.00285  -0.0492   0.6114   0.0351
  -1.500   0.1462   0.01069   0.00270  -0.0492   0.6063   0.0361
  -1.250   0.1741   0.01058   0.00256  -0.0492   0.6014   0.0373
  -1.000   0.2023   0.01046   0.00245  -0.0492   0.5961   0.0388
  -0.750   0.2302   0.01035   0.00233  -0.0492   0.5909   0.0416
  -0.500   0.2581   0.01026   0.00224  -0.0492   0.5857   0.0458
  -0.250   0.2861   0.01013   0.00216  -0.0492   0.5795   0.0562
   0.000   0.3136   0.00999   0.00212  -0.0492   0.5731   0.0838
   0.250   0.3415   0.00989   0.00209  -0.0493   0.5672   0.1085
   0.500   0.3693   0.00979   0.00206  -0.0493   0.5599   0.1376
   0.750   0.3965   0.00963   0.00206  -0.0493   0.5525   0.1913
   1.000   0.4220   0.00919   0.00206  -0.0491   0.5440   0.3438
   1.250   0.4328   0.00759   0.00224  -0.0453   0.5371   0.9191
   1.500   0.4675   0.00773   0.00235  -0.0464   0.5266   0.9544
   1.750   0.5016   0.00787   0.00243  -0.0477   0.5152   0.9705
   2.000   0.5450   0.00805   0.00254  -0.0510   0.5025   0.9800
   2.250   0.5951   0.00825   0.00265  -0.0559   0.4889   0.9881
   2.500   0.6463   0.00846   0.00276  -0.0611   0.4749   0.9953
   2.750   0.6802   0.00858   0.00281  -0.0626   0.4636   0.9970
   3.000   0.7111   0.00869   0.00287  -0.0634   0.4540   0.9982
   3.250   0.7413   0.00883   0.00295  -0.0641   0.4449   0.9993
   3.500   0.7699   0.00895   0.00304  -0.0644   0.4365   1.0000
   3.750   0.7943   0.00909   0.00313  -0.0639   0.4281   1.0000
   4.000   0.8185   0.00924   0.00323  -0.0633   0.4187   1.0000
   4.250   0.8426   0.00938   0.00334  -0.0627   0.4104   1.0000
   4.500   0.8664   0.00954   0.00347  -0.0620   0.4020   1.0000
   4.750   0.8904   0.00967   0.00360  -0.0613   0.3949   1.0000
   5.000   0.9144   0.00981   0.00373  -0.0607   0.3889   1.0000
   5.500   0.9619   0.01010   0.00402  -0.0593   0.3784   1.0000
   5.750   0.9854   0.01025   0.00418  -0.0586   0.3720   1.0000
   6.000   1.0087   0.01043   0.00436  -0.0578   0.3662   1.0000
   6.250   1.0324   0.01057   0.00453  -0.0571   0.3605   1.0000
   6.500   1.0556   0.01075   0.00472  -0.0563   0.3545   1.0000
   6.750   1.0787   0.01093   0.00492  -0.0556   0.3463   1.0000
   7.000   1.1007   0.01118   0.00513  -0.0546   0.3322   1.0000
   7.250   1.1223   0.01146   0.00537  -0.0536   0.3164   1.0000
   7.500   1.1430   0.01179   0.00563  -0.0525   0.2970   1.0000
   7.750   1.1616   0.01226   0.00597  -0.0511   0.2698   1.0000
   8.000   1.1786   0.01285   0.00640  -0.0495   0.2389   1.0000
   8.250   1.1938   0.01356   0.00693  -0.0476   0.2055   1.0000
   8.500   1.2096   0.01424   0.00748  -0.0459   0.1794   1.0000
   8.750   1.2255   0.01491   0.00804  -0.0442   0.1594   1.0000
   9.000   1.2418   0.01553   0.00859  -0.0426   0.1413   1.0000
   9.250   1.2554   0.01629   0.00923  -0.0406   0.1186   1.0000
   9.500   1.2641   0.01729   0.01007  -0.0380   0.0879   1.0000
   9.750   1.2686   0.01832   0.01096  -0.0346   0.0654   1.0000
  10.000   1.2758   0.01924   0.01183  -0.0319   0.0532   1.0000
  10.250   1.2855   0.02012   0.01271  -0.0297   0.0452   1.0000
  10.500   1.2954   0.02108   0.01366  -0.0277   0.0389   1.0000
  10.750   1.3051   0.02212   0.01472  -0.0260   0.0336   1.0000
  11.000   1.3150   0.02322   0.01584  -0.0244   0.0292   1.0000
  11.250   1.3251   0.02438   0.01703  -0.0231   0.0259   1.0000
  11.500   1.3338   0.02571   0.01838  -0.0218   0.0232   1.0000
  11.750   1.3437   0.02700   0.01973  -0.0208   0.0213   1.0000
  12.000   1.3518   0.02850   0.02129  -0.0197   0.0197   1.0000
  12.250   1.3594   0.03012   0.02296  -0.0188   0.0185   1.0000
  12.500   1.3673   0.03175   0.02466  -0.0181   0.0175   1.0000
  12.750   1.3738   0.03356   0.02654  -0.0174   0.0166   1.0000
  13.000   1.3788   0.03557   0.02861  -0.0167   0.0158   1.0000
  13.250   1.3815   0.03783   0.03094  -0.0161   0.0151   1.0000
  13.500   1.3865   0.03993   0.03313  -0.0157   0.0146   1.0000
  13.750   1.3901   0.04219   0.03548  -0.0153   0.0142   1.0000
  14.000   1.3925   0.04460   0.03798  -0.0149   0.0137   1.0000
  14.250   1.3938   0.04717   0.04064  -0.0146   0.0134   1.0000
  14.500   1.3939   0.04994   0.04349  -0.0144   0.0130   1.0000
  14.750   1.3929   0.05289   0.04653  -0.0144   0.0127   1.0000
  15.000   1.3905   0.05611   0.04982  -0.0144   0.0124   1.0000
  15.250   1.3862   0.05964   0.05345  -0.0146   0.0121   1.0000
  15.500   1.3819   0.06327   0.05717  -0.0150   0.0118   1.0000
  15.750   1.3802   0.06663   0.06064  -0.0154   0.0116   1.0000
  16.000   1.3778   0.07016   0.06427  -0.0159   0.0114   1.0000
  16.250   1.3749   0.07384   0.06805  -0.0166   0.0112   1.0000
  16.500   1.3714   0.07763   0.07193  -0.0173   0.0109   1.0000
  16.750   1.3674   0.08154   0.07594  -0.0181   0.0107   1.0000
  17.000   1.3632   0.08554   0.08004  -0.0191   0.0105   1.0000
  17.250   1.3587   0.08963   0.08422  -0.0201   0.0103   1.0000
  17.500   1.3537   0.09380   0.08849  -0.0212   0.0101   1.0000
  17.750   1.3482   0.09810   0.09287  -0.0224   0.0100   1.0000
  18.000   1.3420   0.10254   0.09741  -0.0237   0.0098   1.0000
  18.250   1.3356   0.10707   0.10202  -0.0251   0.0097   1.0000
  18.500   1.3290   0.11167   0.10671  -0.0267   0.0096   1.0000
  18.750   1.3219   0.11636   0.11148  -0.0283   0.0094   1.0000
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