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NACA 22112 (naca22112-jf) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 22112 (naca22112-jf)
Reynolds number: 50,000
Max Cl/Cd: 26.4 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca22112-jf-50000-n5.txt
Download as CSV file: xf-naca22112-jf-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 22112                                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.6993   0.08066   0.07283  -0.0281   1.0000   0.0576
 -10.000  -0.7073   0.07683   0.06892  -0.0275   1.0000   0.0573
  -9.750  -0.7143   0.07296   0.06494  -0.0269   1.0000   0.0569
  -9.500  -0.7204   0.06917   0.06098  -0.0260   1.0000   0.0566
  -9.250  -0.7245   0.06548   0.05708  -0.0248   1.0000   0.0563
  -9.000  -0.7259   0.06192   0.05326  -0.0234   1.0000   0.0561
  -8.750  -0.7245   0.05851   0.04956  -0.0219   1.0000   0.0559
  -8.500  -0.7207   0.05529   0.04600  -0.0201   1.0000   0.0560
  -8.250  -0.7152   0.05237   0.04264  -0.0181   1.0000   0.0566
  -8.000  -0.7074   0.04978   0.03956  -0.0160   1.0000   0.0574
  -7.750  -0.6950   0.04700   0.03650  -0.0144   1.0000   0.0584
  -7.500  -0.6780   0.04441   0.03378  -0.0133   1.0000   0.0594
  -7.250  -0.6607   0.04206   0.03120  -0.0119   1.0000   0.0600
  -7.000  -0.6420   0.03990   0.02879  -0.0105   1.0000   0.0607
  -6.750  -0.6220   0.03794   0.02663  -0.0092   1.0000   0.0619
  -6.500  -0.6014   0.03623   0.02470  -0.0079   1.0000   0.0641
  -6.250  -0.5798   0.03467   0.02288  -0.0066   1.0000   0.0663
  -6.000  -0.5566   0.03321   0.02118  -0.0054   1.0000   0.0680
  -5.750  -0.5319   0.03174   0.01960  -0.0044   1.0000   0.0693
  -5.500  -0.5076   0.03016   0.01812  -0.0036   1.0000   0.0722
  -5.250  -0.4848   0.02902   0.01698  -0.0025   1.0000   0.0759
  -5.000  -0.4625   0.02802   0.01591  -0.0011   1.0000   0.0791
  -4.500  -0.4236   0.02603   0.01389   0.0021   1.0000   0.0863
  -4.250  -0.4054   0.02519   0.01300   0.0038   1.0000   0.0918
  -4.000  -0.3872   0.02441   0.01215   0.0055   1.0000   0.0969
  -3.750  -0.3694   0.02354   0.01130   0.0070   1.0000   0.1055
  -3.500  -0.3511   0.02268   0.01054   0.0084   1.0000   0.1187
  -3.250  -0.3350   0.02134   0.00980   0.0098   1.0000   0.1762
  -3.000  -0.3308   0.01932   0.00970   0.0136   1.0000   0.5047
  -2.750  -0.3169   0.01891   0.00996   0.0176   1.0000   0.6488
  -2.500  -0.2972   0.01897   0.01033   0.0208   1.0000   0.7458
  -2.250  -0.2703   0.01933   0.01079   0.0228   1.0000   0.8225
  -2.000  -0.2178   0.02021   0.01160   0.0210   1.0000   0.9015
  -1.750  -0.1541   0.02074   0.01190   0.0151   1.0000   0.9415
  -1.500  -0.1042   0.02082   0.01180   0.0102   1.0000   0.9593
  -1.250  -0.0405   0.02083   0.01164   0.0024   0.9898   0.9734
  -1.000   0.0287   0.02072   0.01138  -0.0063   0.9742   0.9848
  -0.750   0.0986   0.02049   0.01104  -0.0150   0.9567   0.9944
  -0.500   0.1561   0.02019   0.01067  -0.0213   0.9311   1.0000
  -0.250   0.1980   0.01992   0.01033  -0.0243   0.9002   1.0000
   0.000   0.2338   0.01967   0.01000  -0.0257   0.8665   1.0000
   0.250   0.2636   0.01946   0.00970  -0.0258   0.8309   1.0000
   0.500   0.2890   0.01930   0.00941  -0.0248   0.7943   1.0000
   0.750   0.3114   0.01921   0.00916  -0.0231   0.7576   1.0000
   1.000   0.3317   0.01919   0.00898  -0.0212   0.7200   1.0000
   1.250   0.3516   0.01923   0.00885  -0.0192   0.6828   1.0000
   1.500   0.3714   0.01932   0.00875  -0.0173   0.6464   1.0000
   1.750   0.3911   0.01946   0.00871  -0.0154   0.6108   1.0000
   2.000   0.4108   0.01965   0.00872  -0.0136   0.5758   1.0000
   2.250   0.4306   0.01989   0.00877  -0.0119   0.5417   1.0000
   2.500   0.4503   0.02016   0.00887  -0.0103   0.5085   1.0000
   2.750   0.4699   0.02048   0.00903  -0.0086   0.4757   1.0000
   3.000   0.4895   0.02085   0.00924  -0.0071   0.4440   1.0000
   3.250   0.5099   0.02126   0.00949  -0.0058   0.4139   1.0000
   3.500   0.5302   0.02173   0.00979  -0.0045   0.3863   1.0000
   3.750   0.5506   0.02223   0.01016  -0.0032   0.3610   1.0000
   4.000   0.5713   0.02278   0.01056  -0.0020   0.3396   1.0000
   4.250   0.5924   0.02335   0.01105  -0.0009   0.3197   1.0000
   4.500   0.6134   0.02395   0.01158   0.0002   0.3028   1.0000
   4.750   0.6347   0.02459   0.01212   0.0012   0.2887   1.0000
   5.000   0.6561   0.02524   0.01269   0.0023   0.2767   1.0000
   5.250   0.6778   0.02592   0.01340   0.0032   0.2648   1.0000
   5.500   0.6995   0.02664   0.01412   0.0042   0.2548   1.0000
   5.750   0.7214   0.02737   0.01481   0.0051   0.2462   1.0000
   6.000   0.7434   0.02819   0.01571   0.0060   0.2381   1.0000
   6.250   0.7652   0.02898   0.01650   0.0068   0.2306   1.0000
   6.500   0.7868   0.02988   0.01750   0.0077   0.2234   1.0000
   6.750   0.8084   0.03079   0.01847   0.0086   0.2169   1.0000
   7.000   0.8306   0.03175   0.01943   0.0093   0.2116   1.0000
   7.250   0.8505   0.03287   0.02080   0.0102   0.2051   1.0000
   7.500   0.8717   0.03383   0.02179   0.0110   0.1996   1.0000
   7.750   0.8920   0.03505   0.02313   0.0119   0.1947   1.0000
   8.000   0.9100   0.03644   0.02480   0.0129   0.1894   1.0000
   8.250   0.9302   0.03756   0.02599   0.0137   0.1845   1.0000
   8.500   0.9490   0.03891   0.02745   0.0145   0.1801   1.0000
   8.750   0.9623   0.04074   0.02964   0.0158   0.1752   1.0000
   9.000   0.9788   0.04223   0.03131   0.0168   0.1708   1.0000
   9.250   1.0005   0.04334   0.03236   0.0174   0.1670   1.0000
   9.500   1.0047   0.04587   0.03537   0.0191   0.1626   1.0000
   9.750   1.0114   0.04818   0.03799   0.0206   0.1586   1.0000
  10.000   1.0241   0.04987   0.03983   0.0217   0.1549   1.0000
  10.250   1.0417   0.05129   0.04124   0.0224   0.1514   1.0000
  10.500   1.0252   0.05526   0.04573   0.0247   0.1483   1.0000
  10.750   1.0069   0.05928   0.05008   0.0264   0.1457   1.0000
  11.000   0.9811   0.06364   0.05467   0.0281   0.1438   1.0000
  11.250   0.9302   0.07140   0.06262   0.0266   0.1430   1.0000
  11.500   0.8138   0.09465   0.08590   0.0112   0.1418   1.0000
  11.750   0.8220   0.09692   0.08822   0.0112   0.1391   1.0000
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