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N-22 (n22-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: N-22 (n22-il)
Reynolds number: 50,000
Max Cl/Cd: 24.26 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n22-il-50000.txt
Download as CSV file: xf-n22-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: N-22                                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.3307   0.11470   0.10756  -0.0276   0.9999   0.2401
 -10.750  -0.3082   0.10951   0.10237  -0.0263   0.9999   0.2478
 -10.500  -0.3246   0.10905   0.10204  -0.0264   0.9999   0.2567
 -10.250  -0.3082   0.10459   0.09760  -0.0252   0.9999   0.2635
 -10.000  -0.3216   0.10374   0.09688  -0.0241   0.9999   0.2730
  -9.750  -0.3152   0.10029   0.09350  -0.0228   0.9999   0.2792
  -9.500  -0.3243   0.09901   0.09233  -0.0208   0.9999   0.2891
  -9.250  -0.3307   0.09671   0.09015  -0.0187   0.9999   0.2953
  -9.000  -0.3380   0.09527   0.08882  -0.0158   0.9999   0.3056
  -8.750  -0.3940   0.09720   0.09102  -0.0113   0.9999   0.3087
  -8.500  -0.3650   0.09260   0.08640  -0.0088   0.9999   0.3227
  -8.250  -0.3711   0.09049   0.08438  -0.0056   0.9999   0.3316
  -8.000  -0.4034   0.09054   0.08460  -0.0023   0.9999   0.3416
  -7.750  -0.3952   0.08769   0.08179   0.0011   0.9999   0.3550
  -7.500  -0.4029   0.08577   0.07997   0.0042   0.9999   0.3673
  -7.250  -0.4171   0.08422   0.07851   0.0069   0.9999   0.3812
  -7.000  -0.4263   0.08249   0.07686   0.0098   0.9999   0.3975
  -6.750  -0.4300   0.08051   0.07494   0.0129   0.9999   0.4150
  -6.500  -0.4309   0.07845   0.07294   0.0162   0.9999   0.4341
  -6.250  -0.4332   0.07659   0.07114   0.0197   0.9999   0.4566
  -6.000  -0.4373   0.07466   0.06929   0.0236   0.9999   0.4839
  -5.750  -0.3479   0.04991   0.04230  -0.0397   0.9999   0.1923
  -5.500  -0.3233   0.04686   0.03887  -0.0415   0.9999   0.1879
  -5.250  -0.2986   0.04403   0.03571  -0.0430   0.9999   0.1846
  -5.000  -0.2722   0.04153   0.03276  -0.0446   0.9999   0.1832
  -4.750  -0.2464   0.03974   0.03052  -0.0458   0.9999   0.1867
  -4.500  -0.2195   0.03823   0.02841  -0.0468   0.9999   0.1904
  -4.250  -0.1969   0.03695   0.02709  -0.0471   0.9999   0.1946
  -4.000  -0.1738   0.03619   0.02614  -0.0474   0.9999   0.2028
  -3.750  -0.1493   0.03545   0.02524  -0.0479   0.9995   0.2127
  -3.500  -0.0929   0.03483   0.02441  -0.0538   0.9880   0.2345
  -3.250  -0.0407   0.03432   0.02386  -0.0587   0.9760   0.2669
  -3.000   0.0097   0.03388   0.02351  -0.0631   0.9636   0.3197
  -2.750   0.0603   0.03327   0.02335  -0.0673   0.9514   0.4144
  -2.500   0.0973   0.03075   0.02310  -0.0666   0.9399   1.0001
  -2.250   0.1456   0.03155   0.02306  -0.0710   0.9244   1.0001
  -2.000   0.1873   0.03227   0.02339  -0.0741   0.9088   1.0001
  -1.750   0.2273   0.03294   0.02375  -0.0768   0.8930   1.0001
  -1.500   0.2655   0.03358   0.02414  -0.0791   0.8772   1.0001
  -1.250   0.3024   0.03418   0.02455  -0.0811   0.8615   1.0001
  -1.000   0.3384   0.03475   0.02495  -0.0828   0.8457   1.0001
  -0.750   0.3726   0.03533   0.02538  -0.0842   0.8301   1.0001
  -0.500   0.4063   0.03588   0.02581  -0.0853   0.8145   1.0001
  -0.250   0.4389   0.03643   0.02625  -0.0863   0.7991   1.0001
   0.000   0.4703   0.03700   0.02674  -0.0870   0.7840   1.0001
   0.250   0.5017   0.03753   0.02720  -0.0876   0.7691   1.0001
   0.500   0.5342   0.03801   0.02763  -0.0882   0.7551   1.0001
   0.750   0.5861   0.03763   0.02719  -0.0908   0.7451   1.0001
   1.000   0.6088   0.03839   0.02791  -0.0902   0.7301   1.0001
   1.250   0.6295   0.03931   0.02881  -0.0894   0.7153   1.0001
   1.500   0.6497   0.04031   0.02979  -0.0887   0.7011   1.0001
   1.750   0.6721   0.04123   0.03070  -0.0881   0.6881   1.0001
   2.000   0.7197   0.04054   0.03001  -0.0893   0.6800   1.0001
   2.250   0.7309   0.04218   0.03165  -0.0879   0.6657   1.0001
   2.500   0.7410   0.04398   0.03346  -0.0866   0.6521   1.0001
   2.750   0.7579   0.04539   0.03489  -0.0858   0.6404   1.0001
   3.000   0.7996   0.04492   0.03446  -0.0863   0.6320   1.0001
   3.250   0.7986   0.04767   0.03723  -0.0844   0.6183   1.0001
   3.500   0.7990   0.05043   0.04002  -0.0828   0.6060   1.0001
   3.750   0.8596   0.04830   0.03797  -0.0839   0.5990   1.0001
   4.000   0.8456   0.05219   0.04188  -0.0816   0.5850   1.0001
   4.250   0.8385   0.05574   0.04546  -0.0800   0.5720   1.0001
   4.500   0.9318   0.05019   0.04005  -0.0813   0.5657   1.0001
   4.750   0.9155   0.05425   0.04415  -0.0788   0.5513   1.0001
   5.000   0.8943   0.05926   0.04918  -0.0770   0.5372   1.0001
   5.250   0.8893   0.06277   0.05274  -0.0758   0.5240   1.0001
   5.500   0.9075   0.06393   0.05396  -0.0746   0.5118   1.0001
   5.750   1.0235   0.05460   0.04485  -0.0744   0.5026   1.0001
   6.000   0.9892   0.06061   0.05088  -0.0716   0.4879   1.0001
   6.250   0.9655   0.06646   0.05677  -0.0706   0.4729   1.0001
   6.500   0.9575   0.07055   0.06091  -0.0696   0.4586   1.0001
   6.750   0.9595   0.07348   0.06390  -0.0685   0.4447   1.0001
   7.000   0.9774   0.07451   0.06502  -0.0671   0.4317   1.0001
   7.250   1.1958   0.05334   0.04415  -0.0673   0.4187   1.0001
   7.500   1.2329   0.05267   0.04354  -0.0668   0.4034   1.0001
   7.750   1.2693   0.05232   0.04322  -0.0664   0.3885   1.0001
   8.000   0.9519   0.09196   0.08268  -0.0656   0.3809   1.0001
   8.250   0.9786   0.09213   0.08296  -0.0640   0.3701   1.0001
   8.500   0.9363   0.10208   0.09288  -0.0663   0.3621   1.0001
   8.750   0.9449   0.10521   0.09608  -0.0660   0.3540   1.0001
   9.000   0.9112   0.11409   0.10495  -0.0684   0.3497   1.0001
   9.250   0.9441   0.11399   0.10497  -0.0667   0.3396   1.0001
   9.500   0.9191   0.12235   0.11333  -0.0693   0.3390   1.0001
   9.750   0.9141   0.12854   0.11958  -0.0711   0.3399   1.0001
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