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NACA 16-012 (naca16012-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NACA 16-012 (naca16012-il)
Reynolds number: 1,000,000
Max Cl/Cd: 51.69 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca16012-il-1000000.txt
Download as CSV file: xf-naca16012-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 16-012                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.000  -0.9473   0.06052   0.05829  -0.0662   1.0000   0.0066
 -14.750  -0.9821   0.05354   0.05109  -0.0674   1.0000   0.0066
 -14.500  -1.0072   0.04896   0.04634  -0.0662   1.0000   0.0066
 -14.250  -1.0302   0.04526   0.04245  -0.0636   1.0000   0.0066
 -14.000  -1.0484   0.04247   0.03951  -0.0601   1.0000   0.0066
 -13.750  -1.0624   0.04034   0.03727  -0.0562   1.0000   0.0066
 -13.500  -1.0763   0.03844   0.03523  -0.0517   1.0000   0.0067
 -13.250  -1.0890   0.03679   0.03347  -0.0468   1.0000   0.0068
 -13.000  -1.0997   0.03542   0.03197  -0.0418   1.0000   0.0068
 -12.750  -1.1100   0.03415   0.03059  -0.0365   1.0000   0.0069
 -12.500  -1.1203   0.03296   0.02928  -0.0308   1.0000   0.0069
 -12.250  -1.1131   0.03156   0.02773  -0.0288   0.9991   0.0071
 -12.000  -1.1035   0.02992   0.02590  -0.0271   0.9978   0.0072
 -11.750  -1.0914   0.02839   0.02420  -0.0257   0.9965   0.0074
 -11.500  -1.0767   0.02702   0.02264  -0.0245   0.9954   0.0076
 -11.250  -1.0600   0.02570   0.02114  -0.0236   0.9945   0.0078
 -11.000  -1.0455   0.02455   0.01983  -0.0220   0.9927   0.0081
 -10.750  -1.0283   0.02350   0.01863  -0.0207   0.9907   0.0083
 -10.500  -1.0074   0.02267   0.01767  -0.0202   0.9891   0.0085
 -10.250  -0.9848   0.02185   0.01672  -0.0199   0.9878   0.0087
 -10.000  -0.9682   0.01966   0.01429  -0.0188   0.9868   0.0094
  -9.750  -0.9422   0.01912   0.01370  -0.0192   0.9858   0.0099
  -9.500  -0.9144   0.01867   0.01322  -0.0199   0.9851   0.0104
  -9.250  -0.8864   0.01810   0.01258  -0.0206   0.9844   0.0110
  -9.000  -0.8584   0.01749   0.01188  -0.0213   0.9839   0.0115
  -8.750  -0.8381   0.01703   0.01136  -0.0202   0.9816   0.0118
  -8.500  -0.8204   0.01613   0.01034  -0.0186   0.9788   0.0125
  -8.250  -0.7970   0.01541   0.00958  -0.0182   0.9770   0.0134
  -8.000  -0.7689   0.01506   0.00922  -0.0188   0.9758   0.0143
  -7.750  -0.7404   0.01470   0.00884  -0.0195   0.9748   0.0153
  -7.500  -0.7100   0.01446   0.00856  -0.0205   0.9741   0.0162
  -7.250  -0.6834   0.01368   0.00773  -0.0208   0.9733   0.0180
  -7.000  -0.6524   0.01337   0.00742  -0.0221   0.9727   0.0195
  -6.750  -0.6210   0.01308   0.00712  -0.0233   0.9722   0.0211
  -6.500  -0.5889   0.01292   0.00695  -0.0247   0.9718   0.0221
  -6.250  -0.5620   0.01222   0.00621  -0.0250   0.9711   0.0254
  -6.000  -0.5481   0.01206   0.00604  -0.0222   0.9663   0.0271
  -5.750  -0.5221   0.01182   0.00578  -0.0221   0.9642   0.0288
  -5.500  -0.4933   0.01163   0.00558  -0.0227   0.9628   0.0298
  -5.250  -0.4673   0.01110   0.00500  -0.0226   0.9614   0.0339
  -5.000  -0.4388   0.01081   0.00471  -0.0231   0.9603   0.0367
  -4.750  -0.4098   0.01057   0.00445  -0.0237   0.9593   0.0389
  -4.500  -0.3810   0.01028   0.00415  -0.0242   0.9582   0.0434
  -4.250  -0.3545   0.01001   0.00391  -0.0242   0.9567   0.0522
  -4.000  -0.3413   0.00967   0.00375  -0.0212   0.9517   0.0891
  -3.750  -0.3215   0.00914   0.00350  -0.0199   0.9490   0.1576
  -3.500  -0.3020   0.00848   0.00322  -0.0186   0.9468   0.2531
  -3.250  -0.2854   0.00766   0.00290  -0.0166   0.9446   0.3871
  -3.000  -0.2810   0.00693   0.00269  -0.0119   0.9397   0.5228
  -2.750  -0.2785   0.00619   0.00246  -0.0064   0.9346   0.6530
  -2.500  -0.2640   0.00572   0.00231  -0.0034   0.9320   0.7383
  -2.250  -0.2403   0.00551   0.00225  -0.0024   0.9302   0.7853
  -2.000  -0.2188   0.00545   0.00226  -0.0010   0.9272   0.8131
  -1.750  -0.1961   0.00542   0.00226   0.0001   0.9238   0.8315
  -1.500  -0.1696   0.00538   0.00225   0.0003   0.9213   0.8459
  -1.250  -0.1418   0.00535   0.00223   0.0003   0.9193   0.8595
  -1.000  -0.1129   0.00542   0.00237   0.0003   0.9176   0.8801
  -0.750  -0.0829   0.00554   0.00250   0.0000   0.9160   0.8926
  -0.500  -0.0601   0.00562   0.00260   0.0011   0.9125   0.9001
  -0.250  -0.0316   0.00566   0.00265   0.0009   0.9095   0.9041
   0.000   0.0000   0.00569   0.00268   0.0000   0.9069   0.9069
   0.250   0.0316   0.00566   0.00264  -0.0009   0.9040   0.9095
   0.500   0.0601   0.00562   0.00260  -0.0011   0.9001   0.9125
   0.750   0.0829   0.00554   0.00250   0.0000   0.8926   0.9160
   1.000   0.1129   0.00542   0.00237  -0.0003   0.8803   0.9176
   1.250   0.1417   0.00535   0.00224  -0.0003   0.8598   0.9193
   1.500   0.1695   0.00538   0.00225  -0.0003   0.8458   0.9213
   1.750   0.1961   0.00542   0.00226  -0.0001   0.8316   0.9238
   2.000   0.2187   0.00545   0.00226   0.0011   0.8128   0.9272
   2.250   0.2404   0.00551   0.00225   0.0024   0.7856   0.9302
   2.500   0.2640   0.00572   0.00231   0.0034   0.7385   0.9320
   2.750   0.2785   0.00619   0.00246   0.0063   0.6530   0.9347
   3.000   0.2811   0.00692   0.00269   0.0118   0.5235   0.9397
   3.250   0.2854   0.00766   0.00290   0.0166   0.3865   0.9446
   3.500   0.3020   0.00848   0.00322   0.0186   0.2529   0.9468
   3.750   0.3215   0.00914   0.00350   0.0199   0.1574   0.9490
   4.000   0.3413   0.00967   0.00375   0.0212   0.0889   0.9518
   4.250   0.3546   0.01001   0.00391   0.0242   0.0521   0.9567
   4.500   0.3810   0.01028   0.00415   0.0242   0.0433   0.9582
   4.750   0.4099   0.01057   0.00445   0.0237   0.0389   0.9593
   5.000   0.4390   0.01081   0.00471   0.0231   0.0366   0.9603
   5.250   0.4675   0.01110   0.00500   0.0226   0.0338   0.9614
   5.500   0.4935   0.01163   0.00558   0.0226   0.0298   0.9629
   5.750   0.5221   0.01182   0.00578   0.0221   0.0288   0.9643
   6.000   0.5480   0.01206   0.00604   0.0222   0.0271   0.9663
   6.250   0.5621   0.01222   0.00621   0.0250   0.0254   0.9711
   6.500   0.5891   0.01291   0.00694   0.0246   0.0221   0.9718
   6.750   0.6213   0.01308   0.00712   0.0232   0.0211   0.9723
   7.000   0.6527   0.01336   0.00742   0.0220   0.0195   0.9727
   7.250   0.6837   0.01367   0.00772   0.0208   0.0180   0.9733
   7.500   0.7105   0.01444   0.00854   0.0204   0.0162   0.9741
   7.750   0.7406   0.01470   0.00884   0.0194   0.0153   0.9749
   8.000   0.7691   0.01506   0.00923   0.0188   0.0143   0.9759
   8.250   0.7971   0.01542   0.00959   0.0182   0.0135   0.9771
   8.500   0.8207   0.01611   0.01033   0.0185   0.0125   0.9788
   8.750   0.8380   0.01701   0.01134   0.0202   0.0118   0.9817
   9.000   0.8588   0.01747   0.01187   0.0212   0.0115   0.9839
   9.250   0.8869   0.01808   0.01256   0.0205   0.0109   0.9845
   9.500   0.9148   0.01867   0.01322   0.0198   0.0104   0.9851
   9.750   0.9426   0.01913   0.01371   0.0191   0.0099   0.9858
  10.000   0.9687   0.01966   0.01429   0.0187   0.0094   0.9868
  10.250   0.9846   0.02200   0.01689   0.0199   0.0087   0.9878
  10.500   1.0081   0.02265   0.01765   0.0200   0.0085   0.9891
  10.750   1.0289   0.02353   0.01866   0.0206   0.0083   0.9908
  11.000   1.0462   0.02453   0.01981   0.0218   0.0081   0.9928
  11.250   1.0608   0.02569   0.02113   0.0234   0.0078   0.9945
  11.500   1.0778   0.02697   0.02258   0.0243   0.0076   0.9954
  11.750   1.0920   0.02841   0.02422   0.0256   0.0074   0.9965
  12.000   1.1042   0.02992   0.02591   0.0270   0.0072   0.9978
  12.250   1.1149   0.03143   0.02759   0.0285   0.0071   0.9991
  12.500   1.1206   0.03293   0.02925   0.0308   0.0069   1.0000
  12.750   1.1103   0.03412   0.03056   0.0364   0.0069   1.0000
  13.000   1.1012   0.03528   0.03182   0.0416   0.0068   1.0000
  13.250   1.0890   0.03678   0.03345   0.0468   0.0068   1.0000
  13.500   1.0773   0.03834   0.03513   0.0516   0.0067   1.0000
  13.750   1.0650   0.04011   0.03701   0.0560   0.0066   1.0000
  14.000   1.0485   0.04246   0.03951   0.0602   0.0066   1.0000
  14.250   1.0296   0.04532   0.04253   0.0637   0.0066   1.0000
  14.500   1.0115   0.04853   0.04587   0.0661   0.0065   1.0000
  14.750   0.9856   0.05318   0.05071   0.0674   0.0065   1.0000
  15.000   0.9485   0.06048   0.05824   0.0661   0.0066   1.0000
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