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NACA 0012 AIRFOILS (n0012-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NACA 0012 AIRFOILS (n0012-il)
Reynolds number: 100,000
Max Cl/Cd: 36.68 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n0012-il-100000.txt
Download as CSV file: xf-n0012-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 0012 AIRFOILS                              
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.5002   0.13756   0.13233  -0.0001   1.0000   0.1541
 -12.500  -0.5184   0.13358   0.12838  -0.0027   1.0000   0.1558
 -12.250  -0.7724   0.10051   0.09513  -0.0153   1.0000   0.0866
 -12.000  -0.7713   0.09532   0.08992  -0.0162   1.0000   0.0856
 -11.750  -0.7896   0.08685   0.08144  -0.0207   1.0000   0.0842
 -11.500  -0.8377   0.07511   0.06959  -0.0287   1.0000   0.0813
 -11.250  -0.9695   0.06291   0.05654  -0.0300   1.0000   0.0753
 -11.000  -0.9842   0.05891   0.05220  -0.0278   1.0000   0.0751
 -10.750  -0.9915   0.05467   0.04764  -0.0258   1.0000   0.0753
 -10.500  -0.9911   0.05060   0.04330  -0.0241   1.0000   0.0759
 -10.250  -0.9765   0.04806   0.04077  -0.0233   1.0000   0.0778
 -10.000  -0.9659   0.04582   0.03837  -0.0219   1.0000   0.0802
  -9.750  -0.9597   0.04303   0.03523  -0.0199   1.0000   0.0822
  -9.500  -0.9523   0.04019   0.03192  -0.0177   1.0000   0.0841
  -9.250  -0.9430   0.03777   0.02894  -0.0153   1.0000   0.0861
  -9.000  -0.9245   0.03526   0.02644  -0.0145   1.0000   0.0896
  -8.750  -0.9056   0.03367   0.02473  -0.0134   1.0000   0.0938
  -8.500  -0.8883   0.03189   0.02255  -0.0117   1.0000   0.0978
  -8.250  -0.8673   0.02998   0.02066  -0.0109   1.0000   0.1029
  -8.000  -0.8471   0.02869   0.01923  -0.0096   1.0000   0.1091
  -7.750  -0.8256   0.02707   0.01754  -0.0086   1.0000   0.1157
  -7.500  -0.8050   0.02598   0.01635  -0.0074   1.0000   0.1242
  -7.250  -0.7836   0.02464   0.01512  -0.0064   1.0000   0.1333
  -7.000  -0.7631   0.02348   0.01396  -0.0051   1.0000   0.1447
  -6.750  -0.7430   0.02242   0.01293  -0.0038   1.0000   0.1584
  -6.500  -0.7235   0.02143   0.01204  -0.0023   1.0000   0.1748
  -6.250  -0.7047   0.02050   0.01124  -0.0008   1.0000   0.1953
  -6.000  -0.6862   0.01958   0.01046   0.0008   1.0000   0.2203
  -5.750  -0.6682   0.01875   0.00981   0.0025   1.0000   0.2509
  -5.500  -0.6504   0.01798   0.00927   0.0042   1.0000   0.2860
  -5.250  -0.6324   0.01733   0.00880   0.0060   1.0000   0.3256
  -5.000  -0.6141   0.01674   0.00844   0.0077   1.0000   0.3656
  -4.750  -0.5953   0.01627   0.00813   0.0095   1.0000   0.4067
  -4.500  -0.5761   0.01585   0.00789   0.0112   1.0000   0.4463
  -4.250  -0.5565   0.01550   0.00770   0.0129   1.0000   0.4854
  -4.000  -0.5366   0.01520   0.00752   0.0145   1.0000   0.5246
  -3.750  -0.5162   0.01493   0.00743   0.0162   1.0000   0.5615
  -3.500  -0.4957   0.01471   0.00736   0.0179   1.0000   0.5981
  -3.250  -0.4751   0.01453   0.00732   0.0196   1.0000   0.6345
  -3.000  -0.4545   0.01440   0.00731   0.0214   1.0000   0.6707
  -2.750  -0.4340   0.01432   0.00735   0.0232   1.0000   0.7062
  -2.500  -0.4137   0.01429   0.00742   0.0252   1.0000   0.7415
  -2.250  -0.3935   0.01433   0.00757   0.0272   1.0000   0.7754
  -2.000  -0.3737   0.01444   0.00777   0.0294   1.0000   0.8089
  -1.750  -0.3539   0.01463   0.00801   0.0317   1.0000   0.8421
  -1.500  -0.3320   0.01489   0.00831   0.0335   1.0000   0.8748
  -1.250  -0.3021   0.01527   0.00870   0.0338   1.0000   0.9052
  -1.000  -0.2578   0.01574   0.00913   0.0309   1.0000   0.9317
  -0.750  -0.2041   0.01619   0.00952   0.0259   1.0000   0.9557
  -0.500  -0.1345   0.01658   0.00986   0.0174   1.0000   0.9712
  -0.250  -0.0651   0.01682   0.01007   0.0086   1.0000   0.9860
   0.000   0.0000   0.01693   0.01017   0.0000   1.0000   1.0000
   0.250   0.0651   0.01682   0.01007  -0.0086   0.9860   1.0000
   0.500   0.1344   0.01658   0.00986  -0.0174   0.9712   1.0000
   0.750   0.2040   0.01619   0.00952  -0.0258   0.9557   1.0000
   1.000   0.2578   0.01574   0.00913  -0.0309   0.9317   1.0000
   1.250   0.3020   0.01527   0.00870  -0.0338   0.9053   1.0000
   1.500   0.3320   0.01489   0.00831  -0.0335   0.8748   1.0000
   1.750   0.3538   0.01462   0.00801  -0.0317   0.8421   1.0000
   2.000   0.3737   0.01444   0.00777  -0.0294   0.8089   1.0000
   2.250   0.3934   0.01433   0.00757  -0.0272   0.7754   1.0000
   2.500   0.4136   0.01429   0.00742  -0.0252   0.7415   1.0000
   2.750   0.4339   0.01432   0.00735  -0.0232   0.7063   1.0000
   3.000   0.4544   0.01440   0.00731  -0.0214   0.6707   1.0000
   3.250   0.4750   0.01453   0.00731  -0.0196   0.6346   1.0000
   3.500   0.4957   0.01471   0.00736  -0.0179   0.5981   1.0000
   3.750   0.5162   0.01493   0.00742  -0.0162   0.5615   1.0000
   4.000   0.5365   0.01520   0.00752  -0.0145   0.5247   1.0000
   4.250   0.5565   0.01549   0.00770  -0.0128   0.4854   1.0000
   4.500   0.5761   0.01585   0.00789  -0.0111   0.4463   1.0000
   4.750   0.5953   0.01627   0.00813  -0.0094   0.4068   1.0000
   5.000   0.6141   0.01674   0.00843  -0.0077   0.3656   1.0000
   5.250   0.6323   0.01732   0.00880  -0.0060   0.3257   1.0000
   5.500   0.6503   0.01798   0.00927  -0.0042   0.2860   1.0000
   5.750   0.6681   0.01874   0.00981  -0.0025   0.2509   1.0000
   6.000   0.6862   0.01958   0.01046  -0.0008   0.2203   1.0000
   6.250   0.7046   0.02050   0.01124   0.0008   0.1953   1.0000
   6.500   0.7235   0.02143   0.01204   0.0023   0.1748   1.0000
   6.750   0.7430   0.02242   0.01293   0.0038   0.1584   1.0000
   7.000   0.7631   0.02348   0.01396   0.0051   0.1447   1.0000
   7.250   0.7836   0.02464   0.01512   0.0064   0.1333   1.0000
   7.500   0.8050   0.02598   0.01635   0.0074   0.1242   1.0000
   7.750   0.8256   0.02706   0.01754   0.0086   0.1157   1.0000
   8.000   0.8471   0.02869   0.01923   0.0096   0.1091   1.0000
   8.250   0.8673   0.02998   0.02066   0.0109   0.1029   1.0000
   8.500   0.8884   0.03189   0.02255   0.0117   0.0978   1.0000
   8.750   0.9057   0.03367   0.02473   0.0134   0.0938   1.0000
   9.000   0.9246   0.03526   0.02644   0.0145   0.0896   1.0000
   9.250   0.9431   0.03777   0.02894   0.0153   0.0861   1.0000
   9.500   0.9524   0.04019   0.03192   0.0176   0.0841   1.0000
   9.750   0.9598   0.04303   0.03523   0.0198   0.0822   1.0000
  10.000   0.9661   0.04582   0.03837   0.0219   0.0801   1.0000
  10.250   0.9768   0.04806   0.04076   0.0233   0.0778   1.0000
  10.500   0.9913   0.05061   0.04331   0.0241   0.0759   1.0000
  10.750   0.9917   0.05469   0.04765   0.0257   0.0753   1.0000
  11.000   0.9845   0.05893   0.05222   0.0278   0.0751   1.0000
  11.250   0.9697   0.06293   0.05656   0.0300   0.0753   1.0000
  11.500   0.8378   0.07522   0.06970   0.0285   0.0813   1.0000
  11.750   0.7898   0.08703   0.08162   0.0204   0.0842   1.0000
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