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N-11 (n11-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: N-11 (n11-il)
Reynolds number: 50,000
Max Cl/Cd: 38.09 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n11-il-50000-n5.txt
Download as CSV file: xf-n11-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3298   0.11087   0.10394  -0.0350   1.0000   0.1291
 -10.000  -0.3469   0.10971   0.10294  -0.0356   1.0000   0.1302
  -9.750  -0.3635   0.10831   0.10169  -0.0351   1.0000   0.1305
  -9.500  -0.3333   0.10266   0.09599  -0.0325   1.0000   0.1349
  -9.250  -0.3374   0.10042   0.09384  -0.0311   1.0000   0.1365
  -8.750  -0.3894   0.09215   0.08580  -0.0349   1.0000   0.0851
  -8.500  -0.3884   0.08957   0.08327  -0.0322   1.0000   0.0830
  -8.250  -0.3943   0.08679   0.08056  -0.0313   1.0000   0.0810
  -8.000  -0.4012   0.08363   0.07744  -0.0315   1.0000   0.0789
  -7.500  -0.4126   0.07161   0.06516  -0.0412   1.0000   0.0720
  -7.250  -0.3975   0.06870   0.06227  -0.0422   0.9967   0.0737
  -7.000  -0.3709   0.06502   0.05846  -0.0463   0.9902   0.0755
  -6.750  -0.3399   0.05798   0.05098  -0.0545   0.9832   0.0742
  -6.500  -0.3071   0.05094   0.04320  -0.0617   0.9762   0.0727
  -6.250  -0.2756   0.04680   0.03856  -0.0655   0.9698   0.0728
  -6.000  -0.2439   0.04448   0.03609  -0.0681   0.9634   0.0747
  -5.750  -0.2127   0.04226   0.03359  -0.0705   0.9564   0.0774
  -5.500  -0.1775   0.03946   0.03029  -0.0734   0.9501   0.0792
  -5.250  -0.1432   0.03690   0.02719  -0.0757   0.9436   0.0801
  -5.000  -0.1085   0.03477   0.02457  -0.0776   0.9367   0.0815
  -4.750  -0.0703   0.03295   0.02225  -0.0799   0.9313   0.0836
  -4.500  -0.0393   0.03166   0.02061  -0.0807   0.9229   0.0868
  -4.250  -0.0011   0.03071   0.01959  -0.0830   0.9175   0.0924
  -4.000   0.0280   0.02985   0.01850  -0.0833   0.9083   0.0973
  -3.750   0.0671   0.02885   0.01732  -0.0852   0.9029   0.1030
  -3.500   0.0960   0.02824   0.01662  -0.0854   0.8936   0.1107
  -3.250   0.1365   0.02749   0.01579  -0.0876   0.8882   0.1276
  -3.000   0.1655   0.02700   0.01539  -0.0880   0.8786   0.1560
  -2.750   0.2064   0.02627   0.01485  -0.0905   0.8733   0.2165
  -2.500   0.2338   0.02568   0.01471  -0.0909   0.8633   0.3044
  -2.250   0.2676   0.02442   0.01439  -0.0920   0.8575   0.4866
  -2.000   0.3010   0.02322   0.01415  -0.0915   0.8480   1.0000
  -1.750   0.3340   0.02326   0.01380  -0.0921   0.8376   1.0000
  -1.500   0.3750   0.02302   0.01322  -0.0938   0.8287   1.0000
  -1.250   0.4052   0.02297   0.01292  -0.0938   0.8152   1.0000
  -1.000   0.4350   0.02293   0.01266  -0.0936   0.8018   1.0000
  -0.750   0.4643   0.02294   0.01248  -0.0935   0.7892   1.0000
  -0.500   0.4954   0.02294   0.01230  -0.0937   0.7784   1.0000
  -0.250   0.5262   0.02295   0.01216  -0.0938   0.7676   1.0000
   0.000   0.5512   0.02312   0.01223  -0.0931   0.7546   1.0000
   0.250   0.5774   0.02326   0.01226  -0.0925   0.7419   1.0000
   0.500   0.6049   0.02334   0.01225  -0.0921   0.7297   1.0000
   0.750   0.6345   0.02334   0.01215  -0.0920   0.7183   1.0000
   1.000   0.6613   0.02342   0.01216  -0.0915   0.7054   1.0000
   1.250   0.6866   0.02356   0.01224  -0.0907   0.6914   1.0000
   1.500   0.7123   0.02368   0.01233  -0.0901   0.6776   1.0000
   1.750   0.7384   0.02380   0.01240  -0.0895   0.6636   1.0000
   2.000   0.7648   0.02391   0.01246  -0.0889   0.6493   1.0000
   2.250   0.7913   0.02404   0.01257  -0.0883   0.6348   1.0000
   2.500   0.8176   0.02420   0.01268  -0.0877   0.6199   1.0000
   2.750   0.8436   0.02439   0.01284  -0.0871   0.6047   1.0000
   3.000   0.8692   0.02463   0.01305  -0.0864   0.5891   1.0000
   3.250   0.8944   0.02492   0.01331  -0.0858   0.5735   1.0000
   3.500   0.9191   0.02524   0.01362  -0.0851   0.5576   1.0000
   3.750   0.9434   0.02561   0.01398  -0.0844   0.5418   1.0000
   4.000   0.9670   0.02600   0.01436  -0.0835   0.5258   1.0000
   4.250   0.9900   0.02641   0.01475  -0.0827   0.5097   1.0000
   4.500   1.0126   0.02686   0.01522  -0.0817   0.4941   1.0000
   4.750   1.0348   0.02735   0.01572  -0.0808   0.4792   1.0000
   5.000   1.0569   0.02787   0.01626  -0.0800   0.4653   1.0000
   5.250   1.0793   0.02842   0.01683  -0.0791   0.4524   1.0000
   5.500   1.1026   0.02895   0.01740  -0.0785   0.4406   1.0000
   5.750   1.1238   0.02960   0.01814  -0.0776   0.4287   1.0000
   6.000   1.1443   0.03033   0.01897  -0.0767   0.4174   1.0000
   6.250   1.1664   0.03102   0.01975  -0.0760   0.4071   1.0000
   6.500   1.1896   0.03165   0.02043  -0.0754   0.3972   1.0000
   6.750   1.2080   0.03254   0.02147  -0.0743   0.3864   1.0000
   7.000   1.2292   0.03333   0.02236  -0.0735   0.3767   1.0000
   7.250   1.2513   0.03410   0.02325  -0.0728   0.3673   1.0000
   7.500   1.2675   0.03511   0.02443  -0.0715   0.3566   1.0000
   7.750   1.2859   0.03594   0.02535  -0.0703   0.3458   1.0000
   8.000   1.3064   0.03664   0.02608  -0.0693   0.3347   1.0000
   8.250   1.3160   0.03780   0.02746  -0.0672   0.3232   1.0000
   8.500   1.3289   0.03883   0.02867  -0.0655   0.3124   1.0000
   8.750   1.3467   0.03963   0.02952  -0.0643   0.3023   1.0000
   9.000   1.3526   0.04103   0.03120  -0.0619   0.2926   1.0000
   9.250   1.3632   0.04216   0.03249  -0.0599   0.2836   1.0000
   9.500   1.3704   0.04320   0.03367  -0.0576   0.2738   1.0000
   9.750   1.3673   0.04480   0.03551  -0.0544   0.2638   1.0000
  10.000   1.3666   0.04614   0.03697  -0.0516   0.2534   1.0000
  10.250   1.3653   0.04745   0.03838  -0.0491   0.2425   1.0000
  10.500   1.3559   0.04979   0.04095  -0.0466   0.2322   1.0000
  10.750   1.3490   0.05216   0.04349  -0.0447   0.2223   1.0000
  11.000   1.3448   0.05438   0.04582  -0.0432   0.2128   1.0000
  11.250   1.3377   0.05727   0.04890  -0.0421   0.2035   1.0000
  11.500   1.3295   0.06054   0.05235  -0.0414   0.1945   1.0000
  11.750   1.3230   0.06355   0.05543  -0.0408   0.1848   1.0000
  12.000   1.3121   0.06745   0.05948  -0.0408   0.1749   1.0000
  12.250   1.2990   0.07197   0.06414  -0.0413   0.1651   1.0000
  12.500   1.2875   0.07632   0.06856  -0.0419   0.1548   1.0000
  12.750   1.2738   0.08130   0.07363  -0.0430   0.1444   1.0000
  13.000   1.2554   0.08762   0.08017  -0.0449   0.1351   1.0000
  13.250   1.2394   0.09364   0.08631  -0.0468   0.1254   1.0000
  13.500   1.2258   0.09941   0.09215  -0.0488   0.1158   1.0000
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