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NACA 0012 AIRFOILS (n0012-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NACA 0012 AIRFOILS (n0012-il)
Reynolds number: 500,000
Max Cl/Cd: 61.71 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n0012-il-500000-n5.txt
Download as CSV file: xf-n0012-il-500000-n5.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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -17.750  -1.1683   0.10069   0.09689  -0.0021   1.0000   0.0140
 -17.500  -1.1891   0.09312   0.08920  -0.0060   1.0000   0.0141
 -17.250  -1.2099   0.08573   0.08168  -0.0098   1.0000   0.0141
 -17.000  -1.2297   0.07862   0.07444  -0.0135   1.0000   0.0142
 -16.750  -1.2482   0.07193   0.06762  -0.0169   1.0000   0.0142
 -16.500  -1.2642   0.06573   0.06129  -0.0201   1.0000   0.0143
 -16.250  -1.2774   0.06009   0.05551  -0.0230   1.0000   0.0144
 -16.000  -1.2876   0.05502   0.05031  -0.0256   1.0000   0.0145
 -15.750  -1.2949   0.05052   0.04568  -0.0277   1.0000   0.0146
 -15.500  -1.2995   0.04660   0.04164  -0.0294   1.0000   0.0148
 -15.250  -1.3018   0.04316   0.03807  -0.0306   1.0000   0.0150
 -15.000  -1.3021   0.04016   0.03496  -0.0314   1.0000   0.0152
 -14.750  -1.3008   0.03755   0.03223  -0.0318   1.0000   0.0154
 -14.500  -1.2982   0.03526   0.02983  -0.0317   1.0000   0.0156
 -14.250  -1.2939   0.03328   0.02774  -0.0313   1.0000   0.0159
 -14.000  -1.2885   0.03156   0.02589  -0.0305   1.0000   0.0162
 -13.750  -1.2815   0.03007   0.02429  -0.0295   1.0000   0.0166
 -13.500  -1.2731   0.02878   0.02288  -0.0282   1.0000   0.0169
 -13.250  -1.2678   0.02736   0.02140  -0.0265   1.0000   0.0172
 -13.000  -1.2593   0.02623   0.02021  -0.0247   1.0000   0.0176
 -12.750  -1.2491   0.02528   0.01919  -0.0229   1.0000   0.0180
 -12.500  -1.2378   0.02443   0.01826  -0.0209   1.0000   0.0185
 -12.250  -1.2249   0.02365   0.01740  -0.0191   1.0000   0.0189
 -12.000  -1.2093   0.02289   0.01656  -0.0176   1.0000   0.0195
 -11.750  -1.1925   0.02217   0.01577  -0.0163   1.0000   0.0200
 -11.500  -1.1753   0.02145   0.01497  -0.0150   1.0000   0.0205
 -11.250  -1.1580   0.02071   0.01419  -0.0137   1.0000   0.0212
 -11.000  -1.1389   0.02009   0.01353  -0.0126   1.0000   0.0220
 -10.750  -1.1189   0.01952   0.01291  -0.0116   1.0000   0.0229
 -10.500  -1.0984   0.01898   0.01231  -0.0106   1.0000   0.0238
 -10.250  -1.0782   0.01842   0.01168  -0.0096   1.0000   0.0246
 -10.000  -1.0580   0.01784   0.01108  -0.0085   1.0000   0.0256
  -9.750  -1.0369   0.01734   0.01055  -0.0075   1.0000   0.0267
  -9.500  -1.0154   0.01689   0.01006  -0.0066   1.0000   0.0280
  -9.250  -0.9940   0.01644   0.00956  -0.0055   1.0000   0.0292
  -9.000  -0.9731   0.01596   0.00908  -0.0045   1.0000   0.0308
  -8.750  -0.9517   0.01556   0.00865  -0.0034   1.0000   0.0325
  -8.500  -0.9302   0.01520   0.00824  -0.0023   1.0000   0.0340
  -8.250  -0.9096   0.01477   0.00782  -0.0010   1.0000   0.0360
  -8.000  -0.8883   0.01441   0.00745   0.0001   1.0000   0.0384
  -7.750  -0.8670   0.01408   0.00709   0.0013   1.0000   0.0407
  -7.500  -0.8461   0.01371   0.00674   0.0026   1.0000   0.0437
  -7.250  -0.8248   0.01342   0.00643   0.0038   1.0000   0.0466
  -7.000  -0.8039   0.01308   0.00611   0.0050   1.0000   0.0504
  -6.750  -0.7799   0.01279   0.00582   0.0056   0.9995   0.0547
  -6.500  -0.7471   0.01242   0.00548   0.0044   0.9969   0.0608
  -6.250  -0.7137   0.01209   0.00517   0.0030   0.9945   0.0678
  -6.000  -0.6812   0.01177   0.00488   0.0018   0.9914   0.0761
  -5.750  -0.6486   0.01145   0.00460   0.0006   0.9878   0.0862
  -5.500  -0.6149   0.01112   0.00433  -0.0008   0.9848   0.0986
  -5.250  -0.5817   0.01079   0.00407  -0.0021   0.9814   0.1131
  -5.000  -0.5512   0.01046   0.00382  -0.0028   0.9757   0.1296
  -4.750  -0.5185   0.01014   0.00359  -0.0040   0.9711   0.1496
  -4.500  -0.4888   0.00985   0.00338  -0.0044   0.9640   0.1702
  -4.250  -0.4576   0.00953   0.00317  -0.0052   0.9573   0.1940
  -4.000  -0.4287   0.00925   0.00298  -0.0055   0.9484   0.2186
  -3.750  -0.3988   0.00897   0.00280  -0.0059   0.9395   0.2454
  -3.500  -0.3711   0.00871   0.00264  -0.0058   0.9277   0.2713
  -3.250  -0.3437   0.00847   0.00249  -0.0057   0.9150   0.2982
  -3.000  -0.3166   0.00826   0.00234  -0.0054   0.9008   0.3257
  -2.750  -0.2901   0.00806   0.00221  -0.0050   0.8850   0.3532
  -2.500  -0.2637   0.00789   0.00210  -0.0045   0.8675   0.3801
  -2.250  -0.2373   0.00774   0.00199  -0.0041   0.8486   0.4076
  -2.000  -0.2111   0.00761   0.00189  -0.0036   0.8285   0.4342
  -1.500  -0.1585   0.00741   0.00173  -0.0026   0.7855   0.4872
  -1.250  -0.1321   0.00734   0.00167  -0.0022   0.7625   0.5131
  -1.000  -0.1057   0.00729   0.00162  -0.0017   0.7391   0.5392
  -0.750  -0.0793   0.00724   0.00158  -0.0013   0.7149   0.5648
  -0.500  -0.0529   0.00722   0.00155  -0.0008   0.6905   0.5906
  -0.250  -0.0265   0.00719   0.00154  -0.0004   0.6655   0.6157
   0.000   0.0000   0.00720   0.00153   0.0000   0.6407   0.6407
   0.250   0.0265   0.00719   0.00154   0.0004   0.6155   0.6656
   0.500   0.0529   0.00722   0.00155   0.0008   0.5906   0.6906
   0.750   0.0794   0.00724   0.00158   0.0013   0.5650   0.7147
   1.000   0.1058   0.00729   0.00162   0.0017   0.5393   0.7390
   1.250   0.1321   0.00734   0.00167   0.0022   0.5130   0.7625
   1.500   0.1585   0.00741   0.00173   0.0026   0.4874   0.7855
   1.750   0.1848   0.00751   0.00180   0.0031   0.4607   0.8076
   2.000   0.2111   0.00761   0.00189   0.0036   0.4341   0.8285
   2.250   0.2373   0.00774   0.00199   0.0041   0.4075   0.8487
   2.500   0.2637   0.00789   0.00210   0.0045   0.3803   0.8676
   2.750   0.2901   0.00806   0.00221   0.0050   0.3534   0.8850
   3.000   0.3167   0.00826   0.00234   0.0054   0.3260   0.9008
   3.250   0.3437   0.00848   0.00249   0.0057   0.2980   0.9150
   3.500   0.3711   0.00871   0.00264   0.0058   0.2713   0.9277
   3.750   0.3988   0.00897   0.00280   0.0059   0.2452   0.9395
   4.000   0.4287   0.00925   0.00298   0.0055   0.2186   0.9484
   4.250   0.4576   0.00953   0.00317   0.0052   0.1941   0.9573
   4.500   0.4889   0.00985   0.00338   0.0044   0.1701   0.9640
   4.750   0.5185   0.01014   0.00359   0.0040   0.1497   0.9711
   5.000   0.5512   0.01046   0.00382   0.0028   0.1297   0.9757
   5.250   0.5818   0.01079   0.00406   0.0021   0.1131   0.9814
   5.500   0.6150   0.01112   0.00433   0.0008   0.0986   0.9848
   5.750   0.6487   0.01145   0.00460  -0.0007   0.0862   0.9878
   6.000   0.6813   0.01177   0.00488  -0.0018   0.0761   0.9914
   6.250   0.7138   0.01209   0.00517  -0.0030   0.0678   0.9945
   6.500   0.7472   0.01242   0.00548  -0.0044   0.0608   0.9969
   6.750   0.7799   0.01279   0.00582  -0.0057   0.0547   0.9995
   7.000   0.8038   0.01308   0.00611  -0.0050   0.0504   1.0000
   7.250   0.8247   0.01342   0.00642  -0.0037   0.0467   1.0000
   7.500   0.8461   0.01371   0.00674  -0.0025   0.0437   1.0000
   7.750   0.8670   0.01408   0.00709  -0.0013   0.0407   1.0000
   8.000   0.8883   0.01441   0.00745  -0.0001   0.0384   1.0000
   8.250   0.9096   0.01477   0.00781   0.0010   0.0360   1.0000
   8.500   0.9302   0.01520   0.00824   0.0023   0.0340   1.0000
   8.750   0.9517   0.01556   0.00865   0.0034   0.0325   1.0000
   9.000   0.9731   0.01596   0.00908   0.0045   0.0308   1.0000
   9.250   0.9941   0.01644   0.00956   0.0055   0.0292   1.0000
   9.500   1.0154   0.01689   0.01005   0.0066   0.0280   1.0000
   9.750   1.0370   0.01734   0.01055   0.0075   0.0267   1.0000
  10.000   1.0581   0.01783   0.01108   0.0085   0.0256   1.0000
  10.250   1.0783   0.01842   0.01168   0.0095   0.0246   1.0000
  10.500   1.0986   0.01898   0.01230   0.0106   0.0238   1.0000
  10.750   1.1190   0.01952   0.01291   0.0116   0.0229   1.0000
  11.000   1.1390   0.02009   0.01353   0.0126   0.0220   1.0000
  11.250   1.1582   0.02071   0.01418   0.0137   0.0212   1.0000
  11.500   1.1756   0.02145   0.01497   0.0150   0.0205   1.0000
  11.750   1.1928   0.02217   0.01577   0.0163   0.0200   1.0000
  12.000   1.2097   0.02289   0.01656   0.0176   0.0195   1.0000
  12.250   1.2253   0.02365   0.01740   0.0190   0.0189   1.0000
  12.500   1.2383   0.02443   0.01826   0.0208   0.0185   1.0000
  12.750   1.2496   0.02528   0.01919   0.0228   0.0180   1.0000
  13.000   1.2599   0.02623   0.02021   0.0246   0.0176   1.0000
  13.250   1.2685   0.02736   0.02140   0.0264   0.0172   1.0000
  13.500   1.2740   0.02877   0.02287   0.0281   0.0168   1.0000
  13.750   1.2822   0.03007   0.02429   0.0293   0.0166   1.0000
  14.000   1.2893   0.03156   0.02589   0.0304   0.0162   1.0000
  14.250   1.2950   0.03327   0.02772   0.0311   0.0159   1.0000
  14.500   1.2994   0.03524   0.02981   0.0316   0.0156   1.0000
  14.750   1.3021   0.03752   0.03220   0.0316   0.0154   1.0000
  15.000   1.3035   0.04013   0.03493   0.0312   0.0152   1.0000
  15.250   1.3033   0.04311   0.03803   0.0304   0.0149   1.0000
  15.500   1.3012   0.04654   0.04158   0.0292   0.0148   1.0000
  15.750   1.2967   0.05047   0.04563   0.0275   0.0146   1.0000
  16.000   1.2895   0.05495   0.05023   0.0253   0.0145   1.0000
  16.250   1.2794   0.06003   0.05545   0.0228   0.0144   1.0000
  16.500   1.2662   0.06567   0.06122   0.0199   0.0143   1.0000
  16.750   1.2503   0.07187   0.06756   0.0166   0.0142   1.0000
  17.000   1.2320   0.07855   0.07437   0.0132   0.0142   1.0000
  17.250   1.2122   0.08566   0.08161   0.0095   0.0141   1.0000
  17.500   1.1914   0.09306   0.08914   0.0057   0.0141   1.0000
  17.750   1.1705   0.10066   0.09686   0.0018   0.0140   1.0000
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