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N-22 (n22-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: N-22 (n22-il)
Reynolds number: 50,000
Max Cl/Cd: 36.02 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n22-il-50000-n5.txt
Download as CSV file: xf-n22-il-50000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.3602   0.09712   0.08991  -0.0420   0.9999   0.0862
 -10.500  -0.3645   0.09422   0.08709  -0.0415   0.9999   0.0854
 -10.250  -0.3745   0.09146   0.08444  -0.0408   0.9999   0.0848
 -10.000  -0.3894   0.08891   0.08202  -0.0397   0.9999   0.0845
  -9.750  -0.4042   0.08602   0.07925  -0.0392   0.9999   0.0843
  -9.500  -0.4181   0.08285   0.07616  -0.0392   0.9999   0.0841
  -9.250  -0.4311   0.07941   0.07277  -0.0395   0.9999   0.0840
  -9.000  -0.4424   0.07568   0.06906  -0.0400   0.9999   0.0839
  -8.750  -0.4511   0.07167   0.06502  -0.0408   0.9999   0.0838
  -8.500  -0.4563   0.06748   0.06074  -0.0417   0.9999   0.0836
  -8.250  -0.4428   0.06160   0.05458  -0.0468   0.9951   0.0832
  -8.000  -0.4184   0.05536   0.04790  -0.0531   0.9874   0.0833
  -7.750  -0.3911   0.04991   0.04188  -0.0585   0.9802   0.0848
  -7.500  -0.3608   0.04502   0.03621  -0.0631   0.9734   0.0873
  -7.250  -0.3308   0.04202   0.03279  -0.0657   0.9663   0.0889
  -7.000  -0.2972   0.03978   0.03027  -0.0682   0.9601   0.0906
  -6.750  -0.2662   0.03787   0.02806  -0.0698   0.9527   0.0928
  -6.500  -0.2311   0.03610   0.02592  -0.0721   0.9461   0.0970
  -6.250  -0.1975   0.03428   0.02349  -0.0738   0.9390   0.1014
  -6.000  -0.1640   0.03303   0.02219  -0.0753   0.9318   0.1047
  -5.750  -0.1284   0.03193   0.02091  -0.0771   0.9253   0.1097
  -5.500  -0.0959   0.03094   0.01958  -0.0780   0.9169   0.1169
  -5.250  -0.0560   0.03004   0.01870  -0.0804   0.9116   0.1248
  -5.000  -0.0278   0.02933   0.01781  -0.0805   0.9016   0.1337
  -4.750   0.0134   0.02857   0.01695  -0.0828   0.8960   0.1482
  -4.500   0.0414   0.02804   0.01641  -0.0829   0.8858   0.1631
  -4.250   0.0820   0.02729   0.01573  -0.0851   0.8799   0.1867
  -4.000   0.1095   0.02684   0.01531  -0.0851   0.8689   0.2144
  -3.750   0.1439   0.02620   0.01485  -0.0863   0.8609   0.2542
  -3.500   0.1748   0.02559   0.01451  -0.0868   0.8513   0.3108
  -3.250   0.2032   0.02490   0.01427  -0.0869   0.8412   0.3997
  -3.000   0.2317   0.02381   0.01402  -0.0861   0.8333   0.5749
  -2.750   0.2741   0.02283   0.01384  -0.0866   0.8231   0.9773
  -2.500   0.3097   0.02274   0.01339  -0.0877   0.8136   1.0001
  -2.250   0.3391   0.02275   0.01314  -0.0877   0.8021   1.0001
  -2.000   0.3660   0.02284   0.01300  -0.0873   0.7899   1.0001
  -1.750   0.3963   0.02283   0.01277  -0.0874   0.7792   1.0001
  -1.500   0.4269   0.02280   0.01254  -0.0875   0.7686   1.0001
  -1.250   0.4524   0.02294   0.01253  -0.0868   0.7557   1.0001
  -1.000   0.4800   0.02302   0.01245  -0.0865   0.7439   1.0001
  -0.750   0.5122   0.02292   0.01220  -0.0866   0.7342   1.0001
  -0.500   0.5367   0.02312   0.01229  -0.0859   0.7206   1.0001
  -0.250   0.5623   0.02329   0.01236  -0.0853   0.7076   1.0001
   0.000   0.5894   0.02340   0.01237  -0.0848   0.6953   1.0001
   0.250   0.6195   0.02340   0.01224  -0.0847   0.6845   1.0001
   0.500   0.6441   0.02363   0.01241  -0.0840   0.6707   1.0001
   0.750   0.6688   0.02387   0.01259  -0.0833   0.6569   1.0001
   1.000   0.6942   0.02410   0.01276  -0.0827   0.6438   1.0001
   1.250   0.7208   0.02429   0.01289  -0.0822   0.6313   1.0001
   1.500   0.7491   0.02439   0.01290  -0.0819   0.6196   1.0001
   1.750   0.7729   0.02473   0.01322  -0.0812   0.6058   1.0001
   2.000   0.7970   0.02509   0.01357  -0.0806   0.5925   1.0001
   2.250   0.8219   0.02542   0.01387  -0.0800   0.5799   1.0001
   2.500   0.8484   0.02568   0.01409  -0.0796   0.5683   1.0001
   2.750   0.8743   0.02600   0.01440  -0.0792   0.5566   1.0001
   3.000   0.8972   0.02649   0.01490  -0.0786   0.5440   1.0001
   3.250   0.9216   0.02693   0.01535  -0.0780   0.5325   1.0001
   3.500   0.9490   0.02722   0.01560  -0.0778   0.5225   1.0001
   3.750   0.9709   0.02781   0.01624  -0.0770   0.5104   1.0001
   4.000   0.9936   0.02837   0.01684  -0.0764   0.4991   1.0001
   4.250   1.0190   0.02875   0.01723  -0.0759   0.4885   1.0001
   4.500   1.0419   0.02923   0.01773  -0.0752   0.4766   1.0001
   4.750   1.0621   0.02984   0.01839  -0.0742   0.4639   1.0001
   5.000   1.0834   0.03037   0.01897  -0.0733   0.4516   1.0001
   5.250   1.1062   0.03081   0.01941  -0.0725   0.4398   1.0001
   5.500   1.1278   0.03131   0.01993  -0.0716   0.4277   1.0001
   5.750   1.1451   0.03205   0.02077  -0.0703   0.4152   1.0001
   6.000   1.1637   0.03272   0.02153  -0.0692   0.4032   1.0001
   6.250   1.1844   0.03328   0.02212  -0.0682   0.3918   1.0001
   6.500   1.2027   0.03395   0.02285  -0.0670   0.3800   1.0001
   6.750   1.2168   0.03486   0.02390  -0.0654   0.3680   1.0001
   7.000   1.2328   0.03566   0.02480  -0.0640   0.3564   1.0001
   7.250   1.2516   0.03630   0.02545  -0.0629   0.3452   1.0001
   7.500   1.2626   0.03734   0.02665  -0.0610   0.3333   1.0001
   7.750   1.2731   0.03843   0.02787  -0.0592   0.3218   1.0001
   8.000   1.2864   0.03934   0.02886  -0.0576   0.3108   1.0001
   8.250   1.2966   0.04035   0.02996  -0.0556   0.3001   1.0001
   8.500   1.3002   0.04182   0.03159  -0.0531   0.2895   1.0001
   8.750   1.3102   0.04296   0.03278  -0.0514   0.2797   1.0001
   9.000   1.3158   0.04440   0.03435  -0.0494   0.2698   1.0001
   9.250   1.3185   0.04620   0.03629  -0.0475   0.2606   1.0001
   9.500   1.3316   0.04729   0.03743  -0.0462   0.2526   1.0001
   9.750   1.3281   0.04979   0.04017  -0.0443   0.2445   1.0001
  10.000   1.3427   0.05082   0.04120  -0.0433   0.2373   1.0001
  10.250   1.3338   0.05396   0.04459  -0.0416   0.2302   1.0001
  10.500   1.3441   0.05539   0.04608  -0.0406   0.2237   1.0001
  10.750   1.3371   0.05864   0.04954  -0.0394   0.2178   1.0001
  11.000   1.3343   0.06159   0.05268  -0.0386   0.2123   1.0001
  11.250   1.3507   0.06264   0.05376  -0.0378   0.2072   1.0001
  11.500   1.3229   0.06857   0.06001  -0.0375   0.2028   1.0001
  11.750   1.3100   0.07308   0.06470  -0.0375   0.1982   1.0001
  12.000   1.3346   0.07294   0.06456  -0.0365   0.1929   1.0001
  12.250   1.2717   0.08462   0.07654  -0.0391   0.1899   1.0001
  12.500   1.1434   0.11071   0.10270  -0.0495   0.1839   1.0001
  12.750   1.1817   0.10681   0.09894  -0.0466   0.1809   1.0001
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