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NACA 0012-34 (naca001234-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA 0012-34 (naca001234-il)
Reynolds number: 200,000
Max Cl/Cd: 39.66 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca001234-il-200000-n5.txt
Download as CSV file: xf-naca001234-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 0012-34                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.6731   0.08328   0.07970  -0.0367   1.0000   0.0092
 -11.500  -0.7005   0.07365   0.06988  -0.0429   1.0000   0.0089
 -11.250  -0.7217   0.06737   0.06342  -0.0458   1.0000   0.0087
 -11.000  -0.7401   0.06260   0.05846  -0.0467   1.0000   0.0087
 -10.750  -0.7567   0.05871   0.05438  -0.0462   1.0000   0.0086
 -10.500  -0.7724   0.05536   0.05084  -0.0443   1.0000   0.0086
 -10.250  -0.7876   0.05241   0.04770  -0.0413   1.0000   0.0086
 -10.000  -0.8022   0.04988   0.04497  -0.0372   1.0000   0.0085
  -9.750  -0.8160   0.04752   0.04240  -0.0323   1.0000   0.0085
  -9.500  -0.8260   0.04492   0.03957  -0.0277   1.0000   0.0085
  -9.250  -0.8336   0.04233   0.03672  -0.0231   1.0000   0.0086
  -9.000  -0.8384   0.03975   0.03386  -0.0186   1.0000   0.0086
  -8.750  -0.8401   0.03726   0.03109  -0.0143   1.0000   0.0087
  -8.500  -0.8383   0.03498   0.02854  -0.0104   1.0000   0.0089
  -8.250  -0.8333   0.03298   0.02631  -0.0070   1.0000   0.0091
  -8.000  -0.8255   0.03124   0.02435  -0.0038   1.0000   0.0093
  -7.750  -0.8159   0.03004   0.02299  -0.0010   1.0000   0.0098
  -7.500  -0.8046   0.02901   0.02182   0.0016   1.0000   0.0105
  -7.250  -0.7918   0.02787   0.02050   0.0041   1.0000   0.0112
  -7.000  -0.7772   0.02641   0.01878   0.0064   1.0000   0.0118
  -6.750  -0.7501   0.02459   0.01673   0.0063   0.9982   0.0123
  -6.500  -0.7218   0.02303   0.01498   0.0059   0.9961   0.0129
  -6.250  -0.6937   0.02177   0.01356   0.0054   0.9937   0.0136
  -6.000  -0.6708   0.01997   0.01167   0.0058   0.9905   0.0156
  -5.750  -0.6441   0.01890   0.01051   0.0053   0.9874   0.0177
  -5.500  -0.6174   0.01801   0.00951   0.0051   0.9839   0.0198
  -5.250  -0.5898   0.01733   0.00866   0.0047   0.9800   0.0234
  -5.000  -0.5604   0.01657   0.00782   0.0039   0.9771   0.0291
  -4.750  -0.5342   0.01589   0.00712   0.0037   0.9728   0.0424
  -4.500  -0.5100   0.01482   0.00641   0.0037   0.9684   0.1134
  -4.250  -0.4894   0.01316   0.00573   0.0037   0.9650   0.3116
  -4.000  -0.4740   0.01212   0.00535   0.0055   0.9583   0.4553
  -3.750  -0.4509   0.01137   0.00516   0.0062   0.9543   0.5768
  -3.500  -0.4220   0.01099   0.00513   0.0061   0.9518   0.6685
  -3.250  -0.3984   0.01086   0.00509   0.0071   0.9456   0.7113
  -3.000  -0.3669   0.01079   0.00498   0.0064   0.9419   0.7345
  -2.750  -0.3336   0.01071   0.00485   0.0052   0.9390   0.7538
  -2.500  -0.3049   0.01068   0.00478   0.0051   0.9339   0.7712
  -2.250  -0.2750   0.01064   0.00470   0.0047   0.9289   0.7868
  -2.000  -0.2419   0.01060   0.00461   0.0036   0.9254   0.8005
  -1.750  -0.2134   0.01057   0.00456   0.0035   0.9197   0.8131
  -1.500  -0.1828   0.01056   0.00450   0.0030   0.9143   0.8238
  -1.250  -0.1489   0.01052   0.00444   0.0017   0.9106   0.8333
  -1.000  -0.1221   0.01052   0.00441   0.0020   0.9030   0.8433
  -0.750  -0.0905   0.01048   0.00434   0.0012   0.8976   0.8526
  -0.500  -0.0605   0.01049   0.00435   0.0009   0.8904   0.8602
  -0.250  -0.0305   0.01044   0.00429   0.0005   0.8837   0.8690
   0.000   0.0000   0.01047   0.00432   0.0000   0.8759   0.8759
   0.250   0.0305   0.01044   0.00429  -0.0005   0.8690   0.8837
   0.500   0.0605   0.01049   0.00435  -0.0009   0.8602   0.8904
   0.750   0.0905   0.01048   0.00434  -0.0012   0.8526   0.8976
   1.000   0.1221   0.01052   0.00441  -0.0020   0.8433   0.9030
   1.250   0.1489   0.01052   0.00444  -0.0017   0.8333   0.9106
   1.500   0.1828   0.01056   0.00450  -0.0030   0.8238   0.9143
   1.750   0.2134   0.01057   0.00456  -0.0035   0.8130   0.9198
   2.000   0.2419   0.01060   0.00461  -0.0036   0.8005   0.9254
   2.250   0.2750   0.01064   0.00470  -0.0047   0.7868   0.9289
   2.500   0.3048   0.01067   0.00478  -0.0051   0.7712   0.9339
   2.750   0.3335   0.01071   0.00485  -0.0052   0.7538   0.9390
   3.000   0.3669   0.01078   0.00498  -0.0064   0.7345   0.9419
   3.250   0.3983   0.01086   0.00509  -0.0071   0.7113   0.9456
   3.500   0.4220   0.01098   0.00512  -0.0061   0.6685   0.9518
   3.750   0.4509   0.01137   0.00515  -0.0062   0.5767   0.9543
   4.000   0.4740   0.01212   0.00535  -0.0055   0.4556   0.9583
   4.250   0.4894   0.01316   0.00573  -0.0037   0.3113   0.9650
   4.500   0.5100   0.01482   0.00641  -0.0037   0.1134   0.9684
   4.750   0.5342   0.01588   0.00711  -0.0037   0.0424   0.9728
   5.000   0.5605   0.01656   0.00782  -0.0039   0.0291   0.9771
   5.250   0.5898   0.01733   0.00866  -0.0047   0.0234   0.9801
   5.500   0.6174   0.01800   0.00950  -0.0051   0.0198   0.9839
   5.750   0.6441   0.01889   0.01051  -0.0054   0.0177   0.9875
   6.000   0.6709   0.01997   0.01167  -0.0058   0.0156   0.9905
   6.250   0.6938   0.02177   0.01356  -0.0055   0.0136   0.9938
   6.500   0.7219   0.02303   0.01498  -0.0059   0.0129   0.9961
   6.750   0.7503   0.02459   0.01672  -0.0063   0.0123   0.9982
   7.000   0.7770   0.02640   0.01877  -0.0064   0.0118   1.0000
   7.250   0.7917   0.02785   0.02049  -0.0041   0.0112   1.0000
   7.500   0.8045   0.02900   0.02181  -0.0016   0.0105   1.0000
   7.750   0.8157   0.03006   0.02301   0.0010   0.0098   1.0000
   8.000   0.8254   0.03124   0.02434   0.0038   0.0093   1.0000
   8.250   0.8332   0.03297   0.02629   0.0070   0.0091   1.0000
   8.500   0.8382   0.03497   0.02853   0.0105   0.0089   1.0000
   8.750   0.8401   0.03725   0.03108   0.0143   0.0087   1.0000
   9.000   0.8385   0.03973   0.03383   0.0186   0.0086   1.0000
   9.250   0.8337   0.04233   0.03671   0.0231   0.0086   1.0000
   9.500   0.8262   0.04493   0.03957   0.0277   0.0085   1.0000
   9.750   0.8163   0.04752   0.04240   0.0322   0.0085   1.0000
  10.000   0.8026   0.04989   0.04498   0.0371   0.0085   1.0000
  10.250   0.7881   0.05243   0.04771   0.0412   0.0086   1.0000
  10.500   0.7729   0.05539   0.05087   0.0442   0.0086   1.0000
  10.750   0.7575   0.05872   0.05440   0.0460   0.0086   1.0000
  11.000   0.7405   0.06267   0.05853   0.0466   0.0087   1.0000
  11.250   0.7223   0.06744   0.06349   0.0456   0.0088   1.0000
  11.500   0.7012   0.07373   0.06997   0.0427   0.0089   1.0000
  11.750   0.6737   0.08346   0.07988   0.0364   0.0092   1.0000
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