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MRC-16 (mrc-16-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: MRC-16 (mrc-16-il)
Reynolds number: 50,000
Max Cl/Cd: 31.22 at α=8.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mrc-16-il-50000-n5.txt
Download as CSV file: xf-mrc-16-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MRC-16                                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4046   0.09507   0.08810  -0.0562   1.0000   0.0569
  -9.750  -0.4128   0.09107   0.08418  -0.0568   1.0000   0.0566
  -9.500  -0.4245   0.08700   0.08020  -0.0575   1.0000   0.0563
  -9.250  -0.4418   0.08327   0.07657  -0.0576   1.0000   0.0559
  -9.000  -0.4652   0.08041   0.07380  -0.0560   1.0000   0.0556
  -8.750  -0.4919   0.07818   0.07165  -0.0528   1.0000   0.0552
  -8.500  -0.5159   0.07553   0.06904  -0.0500   1.0000   0.0549
  -8.250  -0.5378   0.07270   0.06620  -0.0472   1.0000   0.0546
  -8.000  -0.5572   0.06971   0.06313  -0.0445   1.0000   0.0543
  -7.750  -0.5731   0.06653   0.05983  -0.0419   1.0000   0.0541
  -7.500  -0.5836   0.06304   0.05613  -0.0400   0.9994   0.0540
  -7.250  -0.5723   0.05772   0.05030  -0.0425   0.9918   0.0541
  -7.000  -0.5566   0.05303   0.04507  -0.0444   0.9846   0.0545
  -6.750  -0.5393   0.04892   0.04029  -0.0455   0.9772   0.0560
  -6.500  -0.5151   0.04566   0.03654  -0.0470   0.9711   0.0581
  -6.250  -0.4912   0.04354   0.03423  -0.0478   0.9642   0.0604
  -6.000  -0.4626   0.04101   0.03126  -0.0490   0.9583   0.0625
  -5.750  -0.4351   0.03883   0.02858  -0.0497   0.9519   0.0657
  -5.500  -0.4058   0.03691   0.02625  -0.0505   0.9455   0.0697
  -5.250  -0.3703   0.03532   0.02452  -0.0524   0.9409   0.0741
  -5.000  -0.3446   0.03408   0.02296  -0.0522   0.9330   0.0796
  -4.750  -0.3104   0.03281   0.02163  -0.0537   0.9277   0.0865
  -4.500  -0.2803   0.03182   0.02041  -0.0540   0.9210   0.0951
  -4.250  -0.2497   0.03086   0.01945  -0.0548   0.9144   0.1062
  -3.750  -0.1899   0.02910   0.01771  -0.0562   0.9008   0.1439
  -3.500  -0.1553   0.02800   0.01684  -0.0580   0.8955   0.1897
  -3.250  -0.1351   0.02692   0.01631  -0.0574   0.8869   0.2785
  -3.000  -0.1108   0.02564   0.01608  -0.0569   0.8808   0.4766
  -2.750  -0.0924   0.02520   0.01634  -0.0538   0.8730   0.6445
  -2.500  -0.0625   0.02527   0.01664  -0.0520   0.8668   0.7755
  -2.250  -0.0113   0.02562   0.01688  -0.0539   0.8636   0.8744
  -2.000   0.0581   0.02606   0.01698  -0.0605   0.8597   0.9358
  -1.750   0.1362   0.02615   0.01669  -0.0701   0.8560   0.9695
  -1.500   0.2095   0.02593   0.01614  -0.0794   0.8518   0.9913
  -1.250   0.2551   0.02570   0.01568  -0.0835   0.8455   1.0000
  -1.000   0.2712   0.02570   0.01553  -0.0821   0.8345   1.0000
  -0.750   0.2854   0.02579   0.01548  -0.0803   0.8234   1.0000
  -0.500   0.3147   0.02562   0.01515  -0.0808   0.8164   1.0000
  -0.250   0.3253   0.02583   0.01524  -0.0783   0.8044   1.0000
   0.000   0.3418   0.02595   0.01525  -0.0766   0.7942   1.0000
   0.250   0.3681   0.02590   0.01506  -0.0764   0.7866   1.0000
   0.500   0.3805   0.02616   0.01523  -0.0740   0.7752   1.0000
   0.750   0.4072   0.02613   0.01509  -0.0738   0.7679   1.0000
   1.000   0.4233   0.02635   0.01523  -0.0719   0.7573   1.0000
   1.250   0.4400   0.02660   0.01540  -0.0701   0.7472   1.0000
   1.500   0.4684   0.02655   0.01526  -0.0700   0.7400   1.0000
   1.750   0.4818   0.02692   0.01557  -0.0677   0.7288   1.0000
   2.000   0.5130   0.02680   0.01538  -0.0680   0.7224   1.0000
   2.250   0.5272   0.02720   0.01574  -0.0658   0.7111   1.0000
   2.500   0.5461   0.02749   0.01599  -0.0644   0.7012   1.0000
   2.750   0.5751   0.02744   0.01590  -0.0642   0.6937   1.0000
   3.000   0.5904   0.02789   0.01633  -0.0623   0.6825   1.0000
   3.250   0.6240   0.02769   0.01611  -0.0628   0.6762   1.0000
   3.500   0.6384   0.02820   0.01663  -0.0607   0.6645   1.0000
   3.750   0.6580   0.02854   0.01697  -0.0594   0.6543   1.0000
   4.000   0.6890   0.02843   0.01687  -0.0595   0.6468   1.0000
   4.250   0.7045   0.02895   0.01742  -0.0576   0.6351   1.0000
   4.500   0.7289   0.02913   0.01761  -0.0569   0.6259   1.0000
   4.750   0.7552   0.02921   0.01774  -0.0564   0.6166   1.0000
   5.000   0.7721   0.02972   0.01829  -0.0547   0.6052   1.0000
   5.250   0.7991   0.02978   0.01838  -0.0543   0.5960   1.0000
   5.500   0.8229   0.02997   0.01863  -0.0535   0.5857   1.0000
   5.750   0.8398   0.03050   0.01924  -0.0518   0.5740   1.0000
   6.000   0.8642   0.03068   0.01948  -0.0511   0.5638   1.0000
   6.250   0.8917   0.03071   0.01956  -0.0506   0.5539   1.0000
   6.500   0.9072   0.03131   0.02027  -0.0489   0.5415   1.0000
   6.750   0.9267   0.03174   0.02078  -0.0476   0.5300   1.0000
   7.000   0.9540   0.03177   0.02087  -0.0471   0.5196   1.0000
   7.250   0.9753   0.03209   0.02130  -0.0459   0.5078   1.0000
   7.500   0.9901   0.03273   0.02204  -0.0441   0.4951   1.0000
   7.750   1.0075   0.03325   0.02266  -0.0426   0.4828   1.0000
   8.000   1.0282   0.03360   0.02309  -0.0414   0.4707   1.0000
   8.250   1.0523   0.03377   0.02335  -0.0405   0.4587   1.0000
   8.500   1.0697   0.03426   0.02394  -0.0389   0.4457   1.0000
   8.750   1.0808   0.03502   0.02481  -0.0367   0.4323   1.0000
   9.000   1.0923   0.03576   0.02566  -0.0345   0.4192   1.0000
   9.250   1.1051   0.03646   0.02647  -0.0325   0.4059   1.0000
   9.500   1.1185   0.03715   0.02725  -0.0306   0.3926   1.0000
   9.750   1.1316   0.03785   0.02803  -0.0288   0.3791   1.0000
  10.000   1.1443   0.03858   0.02884  -0.0269   0.3655   1.0000
  10.250   1.1556   0.03939   0.02972  -0.0250   0.3517   1.0000
  10.500   1.1660   0.04028   0.03069  -0.0231   0.3378   1.0000
  10.750   1.1697   0.04165   0.03216  -0.0209   0.3239   1.0000
  11.000   1.1731   0.04310   0.03372  -0.0188   0.3100   1.0000
  11.250   1.1759   0.04466   0.03537  -0.0169   0.2961   1.0000
  11.500   1.1782   0.04634   0.03713  -0.0151   0.2824   1.0000
  11.750   1.1796   0.04814   0.03902  -0.0134   0.2687   1.0000
  12.000   1.1804   0.05007   0.04105  -0.0119   0.2552   1.0000
  12.250   1.1802   0.05216   0.04319  -0.0105   0.2418   1.0000
  12.500   1.1796   0.05437   0.04546  -0.0093   0.2287   1.0000
  12.750   1.1781   0.05672   0.04784  -0.0082   0.2158   1.0000
  13.000   1.1766   0.05915   0.05029  -0.0073   0.2033   1.0000
  13.250   1.1721   0.06205   0.05326  -0.0066   0.1911   1.0000
  13.500   1.1653   0.06542   0.05674  -0.0063   0.1796   1.0000
  13.750   1.1593   0.06879   0.06019  -0.0061   0.1684   1.0000
  14.000   1.1545   0.07208   0.06351  -0.0060   0.1579   1.0000
  14.250   1.1511   0.07515   0.06655  -0.0059   0.1477   1.0000
  14.500   1.1421   0.07943   0.07100  -0.0064   0.1382   1.0000
  14.750   1.1355   0.08340   0.07504  -0.0069   0.1295   1.0000
  15.000   1.1331   0.08659   0.07814  -0.0072   0.1211   1.0000
  15.250   1.1223   0.09167   0.08345  -0.0084   0.1137   1.0000
  15.500   1.1191   0.09526   0.08701  -0.0091   0.1067   1.0000
  15.750   1.1091   0.10041   0.09234  -0.0106   0.1005   1.0000
  16.000   1.1076   0.10385   0.09574  -0.0113   0.0945   1.0000
  16.250   1.0944   0.10998   0.10212  -0.0136   0.0900   1.0000
  16.500   1.0983   0.11239   0.10441  -0.0140   0.0842   1.0000
  16.750   1.0818   0.11958   0.11187  -0.0171   0.0811   1.0000
  17.000   1.0633   0.12747   0.11999  -0.0208   0.0785   1.0000
  17.250   1.0541   0.13339   0.12601  -0.0236   0.0752   1.0000
  17.500   1.0565   0.13655   0.12914  -0.0248   0.0714   1.0000
  17.750   1.0213   0.14981   0.14262  -0.0322   0.0709   1.0000
  18.000   0.9727   0.16897   0.16177  -0.0431   0.0702   1.0000
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