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NACA 1412 (naca1412-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NACA 1412 (naca1412-il)
Reynolds number: 200,000
Max Cl/Cd: 57.6 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca1412-il-200000.txt
Download as CSV file: xf-naca1412-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 1412                                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.8958   0.06212   0.05756  -0.0507   1.0000   0.0460
 -12.250  -0.9216   0.05755   0.05277  -0.0514   1.0000   0.0459
 -12.000  -0.9456   0.05347   0.04846  -0.0497   1.0000   0.0461
 -11.750  -0.9589   0.04964   0.04446  -0.0477   1.0000   0.0466
 -11.500  -0.9498   0.04782   0.04266  -0.0468   1.0000   0.0477
 -11.250  -0.9376   0.04652   0.04136  -0.0457   1.0000   0.0489
 -11.000  -0.9383   0.04388   0.03849  -0.0438   1.0000   0.0498
 -10.750  -0.9376   0.04113   0.03545  -0.0417   1.0000   0.0507
 -10.500  -0.9341   0.03867   0.03265  -0.0395   1.0000   0.0520
 -10.250  -0.9285   0.03652   0.03010  -0.0372   1.0000   0.0534
 -10.000  -0.9203   0.03482   0.02800  -0.0347   1.0000   0.0544
  -9.750  -0.9080   0.03178   0.02483  -0.0334   1.0000   0.0559
  -9.500  -0.8908   0.03059   0.02361  -0.0321   1.0000   0.0575
  -9.250  -0.8739   0.02950   0.02243  -0.0306   1.0000   0.0593
  -9.000  -0.8574   0.02825   0.02099  -0.0289   1.0000   0.0611
  -8.750  -0.8403   0.02701   0.01950  -0.0272   1.0000   0.0627
  -8.500  -0.8227   0.02623   0.01847  -0.0254   1.0000   0.0641
  -8.250  -0.8043   0.02418   0.01642  -0.0242   1.0000   0.0663
  -8.000  -0.7849   0.02326   0.01548  -0.0229   1.0000   0.0682
  -7.750  -0.7655   0.02239   0.01454  -0.0215   1.0000   0.0702
  -7.500  -0.7459   0.02164   0.01367  -0.0200   1.0000   0.0727
  -7.250  -0.7260   0.02100   0.01289  -0.0185   1.0000   0.0748
  -7.000  -0.7068   0.01971   0.01163  -0.0171   1.0000   0.0774
  -6.750  -0.6874   0.01898   0.01093  -0.0157   1.0000   0.0804
  -6.500  -0.6676   0.01838   0.01029  -0.0143   1.0000   0.0840
  -6.250  -0.6477   0.01774   0.00960  -0.0129   1.0000   0.0883
  -6.000  -0.6287   0.01701   0.00895  -0.0115   1.0000   0.0940
  -5.750  -0.6083   0.01649   0.00838  -0.0102   1.0000   0.1012
  -5.500  -0.5887   0.01583   0.00781  -0.0089   1.0000   0.1118
  -5.250  -0.5684   0.01527   0.00733  -0.0078   1.0000   0.1270
  -5.000  -0.5474   0.01476   0.00693  -0.0068   1.0000   0.1469
  -4.750  -0.5258   0.01434   0.00663  -0.0060   1.0000   0.1705
  -4.500  -0.5038   0.01396   0.00639  -0.0053   1.0000   0.1967
  -4.250  -0.4816   0.01365   0.00621  -0.0046   1.0000   0.2260
  -4.000  -0.4594   0.01338   0.00609  -0.0041   1.0000   0.2587
  -3.750  -0.4189   0.01306   0.00597  -0.0071   0.9955   0.3055
  -3.500  -0.3783   0.01272   0.00587  -0.0102   0.9901   0.3588
  -3.250  -0.3367   0.01239   0.00580  -0.0133   0.9846   0.4185
  -3.000  -0.2984   0.01206   0.00571  -0.0157   0.9777   0.4747
  -2.750  -0.2566   0.01176   0.00564  -0.0186   0.9723   0.5326
  -2.500  -0.2208   0.01147   0.00557  -0.0201   0.9640   0.5859
  -2.250  -0.1788   0.01120   0.00551  -0.0228   0.9591   0.6417
  -2.000  -0.1450   0.01096   0.00547  -0.0237   0.9499   0.6916
  -1.750  -0.1036   0.01073   0.00541  -0.0259   0.9449   0.7411
  -1.500  -0.0721   0.01055   0.00537  -0.0259   0.9349   0.7827
  -1.250  -0.0345   0.01038   0.00530  -0.0270   0.9287   0.8200
  -1.000  -0.0054   0.01029   0.00528  -0.0263   0.9170   0.8520
  -0.750   0.0267   0.01023   0.00524  -0.0261   0.9068   0.8805
  -0.500   0.0614   0.01017   0.00519  -0.0264   0.8968   0.9043
  -0.250   0.0934   0.01017   0.00516  -0.0263   0.8830   0.9261
   0.000   0.1299   0.01017   0.00513  -0.0272   0.8688   0.9430
   0.250   0.1722   0.01018   0.00508  -0.0294   0.8535   0.9553
   0.500   0.2180   0.01017   0.00501  -0.0324   0.8365   0.9651
   0.750   0.2626   0.01015   0.00491  -0.0354   0.8178   0.9753
   1.000   0.3073   0.01014   0.00482  -0.0385   0.7971   0.9853
   1.250   0.3533   0.01012   0.00472  -0.0421   0.7733   0.9948
   1.500   0.3914   0.01010   0.00457  -0.0442   0.7496   1.0000
   1.750   0.4143   0.01009   0.00446  -0.0433   0.7245   1.0000
   2.000   0.4375   0.01012   0.00437  -0.0423   0.7012   1.0000
   2.250   0.4606   0.01018   0.00434  -0.0414   0.6769   1.0000
   2.500   0.4835   0.01027   0.00432  -0.0405   0.6541   1.0000
   2.750   0.5064   0.01038   0.00434  -0.0395   0.6308   1.0000
   3.000   0.5290   0.01052   0.00438  -0.0384   0.6071   1.0000
   3.250   0.5515   0.01067   0.00444  -0.0373   0.5830   1.0000
   3.500   0.5739   0.01084   0.00452  -0.0362   0.5588   1.0000
   3.750   0.5962   0.01104   0.00462  -0.0350   0.5361   1.0000
   4.000   0.6185   0.01123   0.00476  -0.0339   0.5126   1.0000
   4.250   0.6404   0.01147   0.00489  -0.0327   0.4894   1.0000
   4.500   0.6621   0.01169   0.00506  -0.0314   0.4621   1.0000
   4.750   0.6831   0.01195   0.00521  -0.0301   0.4312   1.0000
   5.000   0.7039   0.01225   0.00539  -0.0287   0.3987   1.0000
   5.250   0.7246   0.01258   0.00560  -0.0274   0.3669   1.0000
   5.500   0.7452   0.01294   0.00586  -0.0260   0.3349   1.0000
   5.750   0.7654   0.01337   0.00615  -0.0246   0.3010   1.0000
   6.000   0.7850   0.01387   0.00648  -0.0232   0.2662   1.0000
   6.250   0.8047   0.01443   0.00689  -0.0219   0.2313   1.0000
   6.500   0.8241   0.01504   0.00735  -0.0205   0.1973   1.0000
   6.750   0.8430   0.01576   0.00789  -0.0191   0.1655   1.0000
   7.000   0.8611   0.01658   0.00855  -0.0176   0.1375   1.0000
   7.250   0.8782   0.01751   0.00931  -0.0160   0.1155   1.0000
   7.500   0.8950   0.01850   0.01017  -0.0143   0.1005   1.0000
   7.750   0.9147   0.01924   0.01093  -0.0129   0.0910   1.0000
   8.000   0.9322   0.02024   0.01190  -0.0114   0.0850   1.0000
   8.250   0.9519   0.02104   0.01274  -0.0101   0.0802   1.0000
   8.500   0.9696   0.02216   0.01377  -0.0087   0.0763   1.0000
   8.750   0.9897   0.02311   0.01480  -0.0075   0.0733   1.0000
   9.000   1.0101   0.02396   0.01573  -0.0064   0.0704   1.0000
   9.250   1.0304   0.02492   0.01672  -0.0054   0.0681   1.0000
   9.500   1.0508   0.02609   0.01786  -0.0045   0.0659   1.0000
   9.750   1.0720   0.02771   0.01952  -0.0038   0.0637   1.0000
  10.000   1.0916   0.02868   0.02066  -0.0027   0.0620   1.0000
  10.250   1.1112   0.02986   0.02198  -0.0016   0.0603   1.0000
  10.500   1.1299   0.03102   0.02325  -0.0005   0.0584   1.0000
  10.750   1.1485   0.03219   0.02445   0.0004   0.0566   1.0000
  11.000   1.1695   0.03467   0.02694   0.0006   0.0547   1.0000
  11.250   1.1823   0.03617   0.02870   0.0024   0.0537   1.0000
  11.500   1.1932   0.03763   0.03044   0.0043   0.0524   1.0000
  11.750   1.2031   0.03923   0.03227   0.0062   0.0509   1.0000
  12.000   1.2129   0.04081   0.03401   0.0080   0.0496   1.0000
  12.250   1.2203   0.04240   0.03573   0.0100   0.0484   1.0000
  12.500   1.2289   0.04406   0.03743   0.0117   0.0473   1.0000
  12.750   1.2360   0.04787   0.04135   0.0126   0.0460   1.0000
  13.000   1.2237   0.04994   0.04370   0.0161   0.0456   1.0000
  13.250   1.2098   0.05241   0.04647   0.0188   0.0451   1.0000
  13.500   1.1939   0.05557   0.04991   0.0206   0.0447   1.0000
  13.750   1.1756   0.05939   0.05401   0.0214   0.0443   1.0000
  14.000   1.1544   0.06401   0.05889   0.0211   0.0441   1.0000
  14.250   1.1301   0.06953   0.06467   0.0196   0.0441   1.0000
  14.500   1.1021   0.07617   0.07155   0.0167   0.0441   1.0000
  14.750   1.0699   0.08419   0.07981   0.0122   0.0444   1.0000
  15.000   1.0334   0.09389   0.08971   0.0062   0.0448   1.0000
  15.250   0.9931   0.10542   0.10140  -0.0010   0.0454   1.0000
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