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N-10 (n10-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: N-10 (n10-il)
Reynolds number: 50,000
Max Cl/Cd: 28.82 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n10-il-50000.txt
Download as CSV file: xf-n10-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: N-10                                            
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.3694   0.11382   0.10680  -0.0244   0.9999   0.2337
 -10.500  -0.3478   0.10905   0.10198  -0.0229   0.9999   0.2436
 -10.250  -0.3755   0.10922   0.10235  -0.0241   0.9999   0.2490
 -10.000  -0.3519   0.10430   0.09739  -0.0224   0.9999   0.2623
  -9.750  -0.3426   0.10066   0.09380  -0.0213   0.9999   0.2720
  -9.500  -0.3718   0.10088   0.09423  -0.0206   0.9999   0.2802
  -9.250  -0.3499   0.09626   0.08960  -0.0190   0.9999   0.2934
  -9.000  -0.3492   0.09338   0.08681  -0.0175   0.9999   0.3022
  -8.750  -0.3794   0.09345   0.08709  -0.0146   0.9999   0.3119
  -8.500  -0.3607   0.08931   0.08296  -0.0129   0.9999   0.3239
  -8.000  -0.4089   0.08768   0.08169  -0.0076   0.9999   0.3446
  -7.750  -0.3963   0.08425   0.07827  -0.0042   0.9999   0.3587
  -7.500  -0.3988   0.08197   0.07608  -0.0010   0.9999   0.3738
  -7.250  -0.4088   0.08025   0.07446   0.0023   0.9999   0.3908
  -7.000  -0.4279   0.07909   0.07343   0.0050   0.9999   0.4091
  -6.750  -0.4115   0.07572   0.07008   0.0097   0.9999   0.4303
  -6.500  -0.4320   0.07498   0.06945   0.0132   0.9999   0.4571
  -6.250  -0.4168   0.07172   0.06623   0.0179   0.9999   0.4794
  -6.000  -0.3688   0.05033   0.04291  -0.0378   0.9999   0.1861
  -5.750  -0.3441   0.04551   0.03756  -0.0401   0.9999   0.1716
  -5.500  -0.3208   0.04256   0.03425  -0.0410   0.9999   0.1678
  -5.250  -0.2957   0.03996   0.03120  -0.0420   0.9999   0.1678
  -5.000  -0.2696   0.03765   0.02843  -0.0428   0.9999   0.1679
  -4.750  -0.2431   0.03564   0.02597  -0.0435   0.9999   0.1680
  -4.500  -0.2165   0.03400   0.02385  -0.0439   0.9999   0.1697
  -4.250  -0.1936   0.03290   0.02272  -0.0438   0.9999   0.1759
  -4.000  -0.1687   0.03202   0.02150  -0.0438   0.9999   0.1842
  -3.750  -0.1447   0.03113   0.02054  -0.0437   0.9999   0.1923
  -3.500  -0.1203   0.03042   0.01967  -0.0436   0.9999   0.2047
  -3.250  -0.0968   0.02988   0.01916  -0.0434   0.9999   0.2260
  -3.000  -0.0706   0.02926   0.01856  -0.0435   0.9999   0.2611
  -2.750  -0.0400   0.02811   0.01803  -0.0442   0.9999   0.3623
  -2.500  -0.0287   0.02516   0.01756  -0.0395   0.9999   1.0001
  -2.250   0.0105   0.02607   0.01771  -0.0427   0.9944   1.0001
  -2.000   0.0662   0.02711   0.01822  -0.0490   0.9783   1.0001
  -1.750   0.1182   0.02803   0.01877  -0.0545   0.9622   1.0001
  -1.500   0.1690   0.02884   0.01928  -0.0595   0.9458   1.0001
  -1.250   0.2204   0.02955   0.01974  -0.0645   0.9292   1.0001
  -1.000   0.2649   0.03009   0.02011  -0.0680   0.9109   1.0001
  -0.750   0.3064   0.03055   0.02043  -0.0708   0.8914   1.0001
  -0.500   0.3529   0.03089   0.02065  -0.0742   0.8723   1.0001
  -0.250   0.4034   0.03103   0.02071  -0.0779   0.8538   1.0001
   0.000   0.4449   0.03119   0.02081  -0.0800   0.8332   1.0001
   0.250   0.4863   0.03124   0.02082  -0.0818   0.8121   1.0001
   0.500   0.5331   0.03102   0.02056  -0.0840   0.7934   1.0001
   0.750   0.5768   0.03075   0.02027  -0.0856   0.7755   1.0001
   1.000   0.6179   0.03048   0.01998  -0.0866   0.7583   1.0001
   1.250   0.6404   0.03100   0.02048  -0.0855   0.7362   1.0001
   1.500   0.6719   0.03112   0.02059  -0.0854   0.7187   1.0001
   1.750   0.7021   0.03135   0.02081  -0.0852   0.7027   1.0001
   2.000   0.7298   0.03179   0.02126  -0.0849   0.6880   1.0001
   2.250   0.7567   0.03231   0.02180  -0.0845   0.6744   1.0001
   2.500   0.7870   0.03264   0.02212  -0.0845   0.6626   1.0001
   2.750   0.8166   0.03303   0.02254  -0.0844   0.6515   1.0001
   3.000   0.8310   0.03460   0.02419  -0.0833   0.6389   1.0001
   3.250   0.8482   0.03603   0.02568  -0.0825   0.6277   1.0001
   3.500   0.8847   0.03602   0.02570  -0.0830   0.6197   1.0001
   3.750   0.8882   0.03854   0.02833  -0.0813   0.6077   1.0001
   4.000   0.9045   0.03993   0.02982  -0.0802   0.5962   1.0001
   4.250   0.9365   0.03958   0.02952  -0.0794   0.5825   1.0001
   4.500   0.9680   0.03906   0.02904  -0.0783   0.5673   1.0001
   4.750   0.9984   0.03871   0.02876  -0.0773   0.5526   1.0001
   5.000   1.0340   0.03821   0.02830  -0.0770   0.5401   1.0001
   5.250   1.0528   0.03907   0.02929  -0.0757   0.5268   1.0001
   5.500   1.0695   0.04010   0.03048  -0.0742   0.5133   1.0001
   5.750   1.0903   0.04075   0.03126  -0.0728   0.4991   1.0001
   6.000   1.1133   0.04124   0.03187  -0.0716   0.4845   1.0001
   6.250   1.1390   0.04155   0.03229  -0.0705   0.4690   1.0001
   6.500   1.1713   0.04134   0.03214  -0.0698   0.4515   1.0001
   6.750   1.1990   0.04160   0.03244  -0.0688   0.4326   1.0001
   7.000   1.2107   0.04317   0.03417  -0.0666   0.4136   1.0001
   7.250   1.2262   0.04478   0.03589  -0.0648   0.3958   1.0001
   7.500   1.2401   0.04668   0.03795  -0.0631   0.3798   1.0001
   7.750   1.2517   0.04876   0.04017  -0.0613   0.3655   1.0001
   8.000   1.2664   0.05067   0.04220  -0.0598   0.3524   1.0001
   8.250   1.2933   0.05193   0.04352  -0.0594   0.3400   1.0001
   8.500   1.2486   0.05799   0.04997  -0.0542   0.3341   1.0001
   8.750   1.2741   0.05911   0.05119  -0.0534   0.3228   1.0001
   9.000   1.1952   0.06828   0.06050  -0.0481   0.3223   1.0001
   9.750   1.3742   0.05475   0.04700  -0.0469   0.2500   1.0001
  10.000   1.3744   0.05421   0.04650  -0.0432   0.2328   1.0001
  10.250   1.2885   0.06768   0.06055  -0.0384   0.2517   1.0001
  10.500   1.2534   0.07426   0.06724  -0.0369   0.2501   1.0001
  11.250   1.3492   0.06078   0.05226  -0.0265   0.1374   1.0001
  11.500   1.3238   0.06554   0.05746  -0.0246   0.1327   1.0001
  11.750   1.1828   0.09186   0.08518  -0.0346   0.1947   1.0001
  12.000   1.2978   0.07448   0.06668  -0.0227   0.1191   1.0001
  12.250   1.2755   0.08011   0.07258  -0.0229   0.1165   1.0001
  12.500   1.1256   0.11129   0.10466  -0.0397   0.1659   1.0001
  12.750   1.1195   0.11504   0.10838  -0.0399   0.1512   1.0001
  13.500   0.9718   0.17219   0.16499  -0.0702   0.1796   1.0001
  13.750   0.9579   0.18055   0.17329  -0.0749   0.1805   1.0001
  14.000   0.9519   0.18744   0.18017  -0.0784   0.1807   1.0001
  14.250   0.9574   0.19375   0.18649  -0.0801   0.1791   1.0001
  14.500   0.6702   0.18065   0.17376  -0.0578   0.2781   1.0001
  14.750   0.6749   0.18381   0.17699  -0.0580   0.2634   1.0001
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