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N-11 (n11-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: N-11 (n11-il)
Reynolds number: 100,000
Max Cl/Cd: 54.61 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n11-il-100000.txt
Download as CSV file: xf-n11-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: N-11                                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3414   0.10552   0.10072  -0.0360   1.0000   0.1053
  -9.750  -0.3705   0.10547   0.10085  -0.0354   1.0000   0.1058
  -9.500  -0.3984   0.10494   0.10046  -0.0351   1.0000   0.1061
  -9.250  -0.3476   0.09686   0.09226  -0.0311   1.0000   0.1093
  -9.000  -0.3503   0.09489   0.09036  -0.0284   1.0000   0.1115
  -8.750  -0.3636   0.09362   0.08918  -0.0254   1.0000   0.1132
  -8.500  -0.3825   0.09264   0.08831  -0.0221   1.0000   0.1148
  -8.250  -0.3993   0.09122   0.08698  -0.0206   1.0000   0.1170
  -8.000  -0.4225   0.08972   0.08555  -0.0237   1.0000   0.1199
  -7.750  -0.4373   0.08622   0.08205  -0.0297   1.0000   0.1217
  -7.500  -0.4309   0.08357   0.07949  -0.0224   1.0000   0.1236
  -7.250  -0.4283   0.08160   0.07756  -0.0192   1.0000   0.1267
  -7.000  -0.4281   0.07916   0.07513  -0.0198   1.0000   0.1314
  -6.750  -0.4120   0.07385   0.06969  -0.0294   0.9968   0.1383
  -6.500  -0.3844   0.07064   0.06648  -0.0306   0.9915   0.1432
  -6.250  -0.3462   0.06524   0.06088  -0.0412   0.9843   0.1548
  -6.000  -0.3110   0.06123   0.05663  -0.0487   0.9762   0.1691
  -5.750  -0.2793   0.05846   0.05390  -0.0502   0.9711   0.1782
  -5.500  -0.2499   0.05495   0.05027  -0.0543   0.9626   0.1897
  -5.250  -0.2096   0.05149   0.04664  -0.0599   0.9571   0.2054
  -5.000  -0.1401   0.03677   0.02984  -0.0741   0.9528   0.1040
  -4.750  -0.1013   0.03377   0.02642  -0.0770   0.9464   0.1015
  -4.500  -0.0542   0.03077   0.02281  -0.0809   0.9425   0.0979
  -4.250  -0.0205   0.02902   0.02063  -0.0821   0.9341   0.0975
  -4.000   0.0241   0.02759   0.01887  -0.0851   0.9288   0.0999
  -3.750   0.0583   0.02674   0.01774  -0.0862   0.9202   0.1044
  -3.500   0.1014   0.02547   0.01635  -0.0889   0.9145   0.1088
  -3.250   0.1363   0.02469   0.01557  -0.0902   0.9057   0.1156
  -3.000   0.1824   0.02359   0.01454  -0.0931   0.8993   0.1305
  -2.750   0.2184   0.02261   0.01377  -0.0943   0.8888   0.1704
  -2.500   0.2708   0.02087   0.01266  -0.0983   0.8835   0.3008
  -2.250   0.3124   0.01841   0.01237  -0.0993   0.8751   1.0000
  -2.000   0.3598   0.01799   0.01154  -0.1021   0.8687   1.0000
  -1.750   0.3897   0.01798   0.01130  -0.1022   0.8575   1.0000
  -1.500   0.4331   0.01760   0.01070  -0.1044   0.8517   1.0000
  -1.250   0.4614   0.01759   0.01053  -0.1041   0.8401   1.0000
  -1.000   0.4916   0.01754   0.01035  -0.1041   0.8294   1.0000
  -0.750   0.5304   0.01720   0.00985  -0.1053   0.8220   1.0000
  -0.500   0.5566   0.01725   0.00980  -0.1046   0.8094   1.0000
  -0.250   0.5850   0.01725   0.00971  -0.1042   0.7978   1.0000
   0.000   0.6185   0.01706   0.00940  -0.1046   0.7883   1.0000
   0.250   0.6461   0.01705   0.00930  -0.1040   0.7756   1.0000
   0.500   0.6718   0.01710   0.00929  -0.1032   0.7620   1.0000
   0.750   0.6981   0.01713   0.00925  -0.1024   0.7485   1.0000
   1.000   0.7250   0.01713   0.00918  -0.1018   0.7349   1.0000
   1.250   0.7521   0.01710   0.00909  -0.1011   0.7208   1.0000
   1.500   0.7790   0.01706   0.00899  -0.1004   0.7058   1.0000
   1.750   0.8056   0.01704   0.00890  -0.0996   0.6901   1.0000
   2.000   0.8320   0.01705   0.00885  -0.0989   0.6735   1.0000
   2.250   0.8585   0.01707   0.00878  -0.0982   0.6558   1.0000
   2.500   0.8855   0.01710   0.00868  -0.0974   0.6370   1.0000
   2.750   0.9102   0.01725   0.00873  -0.0965   0.6161   1.0000
   3.000   0.9343   0.01746   0.00885  -0.0954   0.5945   1.0000
   3.250   0.9596   0.01772   0.00897  -0.0947   0.5748   1.0000
   3.500   0.9843   0.01807   0.00922  -0.0940   0.5563   1.0000
   3.750   1.0076   0.01848   0.00960  -0.0931   0.5380   1.0000
   4.000   1.0315   0.01889   0.00996  -0.0924   0.5212   1.0000
   4.250   1.0556   0.01933   0.01035  -0.0917   0.5059   1.0000
   4.500   1.0800   0.01979   0.01078  -0.0911   0.4919   1.0000
   4.750   1.1051   0.02026   0.01119  -0.0907   0.4791   1.0000
   5.000   1.1286   0.02076   0.01171  -0.0900   0.4661   1.0000
   5.250   1.1515   0.02129   0.01228  -0.0893   0.4533   1.0000
   5.500   1.1742   0.02179   0.01282  -0.0885   0.4403   1.0000
   5.750   1.1969   0.02227   0.01331  -0.0877   0.4272   1.0000
   6.000   1.2198   0.02278   0.01380  -0.0870   0.4145   1.0000
   6.250   1.2438   0.02331   0.01430  -0.0865   0.4024   1.0000
   6.500   1.2654   0.02392   0.01498  -0.0856   0.3904   1.0000
   6.750   1.2865   0.02460   0.01575  -0.0847   0.3787   1.0000
   7.000   1.3082   0.02527   0.01646  -0.0839   0.3669   1.0000
   7.250   1.3314   0.02596   0.01714  -0.0833   0.3555   1.0000
   7.500   1.3527   0.02658   0.01776  -0.0825   0.3429   1.0000
   7.750   1.3694   0.02716   0.01844  -0.0809   0.3292   1.0000
   8.000   1.3851   0.02772   0.01909  -0.0791   0.3154   1.0000
   8.250   1.4002   0.02829   0.01977  -0.0773   0.3022   1.0000
   8.500   1.4153   0.02886   0.02042  -0.0756   0.2900   1.0000
   8.750   1.4309   0.02940   0.02101  -0.0739   0.2785   1.0000
   9.000   1.4433   0.02994   0.02167  -0.0718   0.2670   1.0000
   9.250   1.4506   0.03048   0.02240  -0.0689   0.2547   1.0000
   9.500   1.4566   0.03104   0.02314  -0.0659   0.2427   1.0000
   9.750   1.4591   0.03163   0.02384  -0.0623   0.2312   1.0000
  10.000   1.4598   0.03237   0.02468  -0.0588   0.2191   1.0000
  10.250   1.4587   0.03335   0.02575  -0.0555   0.2058   1.0000
  10.500   1.4565   0.03463   0.02714  -0.0524   0.1906   1.0000
  10.750   1.4529   0.03629   0.02889  -0.0497   0.1735   1.0000
  11.000   1.4452   0.03854   0.03114  -0.0472   0.1538   1.0000
  11.250   1.4344   0.04147   0.03408  -0.0451   0.1273   1.0000
  11.500   1.4173   0.04534   0.03779  -0.0433   0.1018   1.0000
  11.750   1.3972   0.04987   0.04218  -0.0420   0.0888   1.0000
  12.000   1.3782   0.05461   0.04692  -0.0411   0.0795   1.0000
  12.250   1.3608   0.05943   0.05178  -0.0406   0.0733   1.0000
  12.500   1.3472   0.06404   0.05648  -0.0405   0.0679   1.0000
  12.750   1.3337   0.06867   0.06108  -0.0405   0.0645   1.0000
  13.000   1.3278   0.07257   0.06515  -0.0404   0.0605   1.0000
  13.250   1.3218   0.07652   0.06917  -0.0406   0.0574   1.0000
  13.500   1.3173   0.08005   0.07263  -0.0405   0.0548   1.0000
  13.750   1.3162   0.08348   0.07623  -0.0405   0.0523   1.0000
  14.000   1.3151   0.08692   0.07979  -0.0407   0.0500   1.0000
  14.250   1.3149   0.09018   0.08310  -0.0409   0.0480   1.0000
  14.500   1.3218   0.09201   0.08484  -0.0399   0.0460   1.0000
  14.750   1.3277   0.09440   0.08735  -0.0391   0.0448   1.0000
  15.000   1.3294   0.09764   0.09081  -0.0390   0.0439   1.0000
  15.250   1.3296   0.10122   0.09458  -0.0393   0.0432   1.0000
  15.500   1.3268   0.10536   0.09893  -0.0400   0.0426   1.0000
  15.750   1.3210   0.11012   0.10390  -0.0414   0.0422   1.0000
  16.000   1.3118   0.11556   0.10956  -0.0434   0.0418   1.0000
  16.250   1.2989   0.12185   0.11608  -0.0463   0.0417   1.0000
  16.500   1.2810   0.12944   0.12392  -0.0503   0.0418   1.0000
  16.750   1.2566   0.13886   0.13361  -0.0559   0.0422   1.0000
  17.000   1.2249   0.15067   0.14568  -0.0634   0.0431   1.0000
  17.250   1.1884   0.16471   0.15989  -0.0725   0.0443   1.0000
  17.500   1.1559   0.17905   0.17432  -0.0814   0.0454   1.0000
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